Console Output

Skipping 3,578 KB.. Full Log
    executing [  85] ifthen:             0.00000  EQ      1.00000  and  ...
    executing [  88] ifthen:             1.00000  NE      0.00000  OR  ...
    executing [  89] set:            makeWingOml  1
                          makeWingOml =     1.00000     0.00000
    executing [  90] set:            makeWingWaffle  1
                          makeWingWaffle =     1.00000     0.00000
    executing [  92] ifthen:             0.00000  EQ      1.00000  and  ...
    executing [  95] ifthen:             0.00000  NE      0.00000  and  ...
    executing [ 101] ifthen:             1.00000  EQ      1.00000  and      0.00000  eq      0.00000
    executing [ 102] set:            COMP:Fuse  0
                          COMP:Fuse =     0.00000     0.00000
    executing [ 104] ifthen:             0.00000  EQ      1.00000  and  ...
    executing [ 107] ifthen:             1.00000  EQ      1.00000  and      0.00000  eq      0.00000
    executing [ 108] set:            COMP:Htail  0
                          COMP:Htail =     0.00000     0.00000
    executing [ 110] ifthen:             1.00000  EQ      1.00000  and      0.00000  eq      0.00000
    executing [ 111] set:            COMP:Vtail  0
                          COMP:Vtail =     0.00000     0.00000
    executing [ 113] ifthen:             1.00000  EQ      1.00000  and      0.00000  eq      0.00000
    executing [ 114] set:            COMP:Pylon  0
                          COMP:Pylon =     0.00000     0.00000
    executing [ 116] ifthen:             1.00000  EQ      1.00000  and      0.00000  eq      0.00000
    executing [ 117] set:            COMP:Pod  0
                          COMP:Pod =     0.00000     0.00000
    executing [ 119] ifthen:             1.00000  EQ      1.00000  and      0.00000  eq      0.00000
    executing [ 120] set:            COMP:Control  0
                          COMP:Control =     0.00000     0.00000
    executing [ 122] ifthen:             0.00000  EQ      0.00000  and      0.00000  eq      0.00000
    executing [ 123] set:            makeFuseOml  0
                          makeFuseOml =     0.00000     0.00000
    executing [ 124] set:            makeFuseWaffle  0
                          makeFuseWaffle =     0.00000     0.00000
    executing [ 125] set:            makeFuseCmass  0
                          makeFuseCmass =     0.00000     0.00000
    executing [ 127] ifthen:             1.00000  EQ      0.00000  and  ...
    executing [ 133] ifthen:             0.00000  EQ      0.00000  and      0.00000  eq      0.00000
    executing [ 134] set:            makeHtailOml  0
                          makeHtailOml =     0.00000     0.00000
    executing [ 135] set:            makeHtailHinge  0
                          makeHtailHinge =     0.00000     0.00000
    executing [ 136] set:            makeHtailWaffle  0
                          makeHtailWaffle =     0.00000     0.00000
    executing [ 137] set:            makeHtailCmass  0
                          makeHtailCmass =     0.00000     0.00000
    executing [ 139] ifthen:             0.00000  EQ      0.00000  and      0.00000  eq      0.00000
    executing [ 140] set:            makeVtailOml  0
                          makeVtailOml =     0.00000     0.00000
    executing [ 141] set:            makeVtailHinge  0
                          makeVtailHinge =     0.00000     0.00000
    executing [ 142] set:            makeVtailWaffle  0
                          makeVtailWaffle =     0.00000     0.00000
    executing [ 143] set:            makeVtailCmass  0
                          makeVtailCmass =     0.00000     0.00000
    executing [ 145] ifthen:             0.00000  EQ      0.00000  and      0.00000  eq      0.00000
    executing [ 146] set:            makePylonOml  0
                          makePylonOml =     0.00000     0.00000
    executing [ 148] ifthen:             0.00000  EQ      0.00000  and      0.00000  eq      0.00000
    executing [ 149] set:            makePodOml  0
                          makePodOml =     0.00000     0.00000
    executing [ 151] ifthen:             0.00000  EQ      0.00000  and      0.00000  eq      0.00000
    executing [ 152] set:            makeWingHinge  0
                          makeWingHinge =     0.00000     0.00000
    executing [ 153] set:            makeHtailHinge  0
                          makeHtailHinge =     0.00000     0.00000
    executing [ 154] set:            makeVtailHinge  0
                          makeVtailHinge =     0.00000     0.00000
    executing [ 156] end:
    executing [ 157] set:            wing:span  sqrt(wing:aspect*wing:area)
                          wing:span =     7.74597     0.00000
    executing [ 158] set:            wing:chordr  2*wing:area/wing:span/(1+wing:taper)
                          wing:chordr =     1.61374     0.00000
    executing [ 159] set:            wing:chordt  wing:chordr*wing:taper
                          wing:chordt =     0.96825     0.00000
    executing [ 160] set:            wing:ytip  -wing:span/2
                          wing:ytip =    -3.87298     0.00000
    executing [ 161] set:            wing:xtip  -wing:ytip*tand(wing:sweep)
                          wing:xtip =     1.40965     0.00000
    executing [ 162] set:            wing:ztip  -wing:ytip*tand(wing:dihedral)
                          wing:ztip =     0.27083     0.00000
    executing [ 163] set:            wing:mac  sqrt(wing:area/wing:aspect)
                          wing:mac =     1.29099     0.00000
    executing [ 164] ifthen:             1.00000  EQ      1.00000  and      0.00000  eq      0.00000
    executing [ 165] mark:
                          Mark        created
    executing [ 166] udprim:     naca thickness     0.12000 camber     0.06000 sharpte     0.00000 (compiled code)
                          Body      1 created  (toler= 1.0000e-07, nnode=   3, nedge=   3, nface=   1)
    executing [ 167] scale:          1.61374      0.00000      0.00000      0.00000
                          Body      2 created  (toler= 1.6137e-07, nnode=   3, nedge=   3, nface=   1)
    executing [ 168] rotatex:       90.00000      0.00000      0.00000
                          Body      3 created  (toler= 1.6137e-07, nnode=   3, nedge=   3, nface=   1)
    executing [ 169] udprim:     naca thickness     0.16000 camber     0.02000 sharpte     0.00000 (compiled code)
                          Body      4 created  (toler= 1.0000e-07, nnode=   3, nedge=   3, nface=   1)
    executing [ 170] scale:          0.96825      0.00000      0.00000      0.00000
                          Body      5 created  (toler= 1.0000e-07, nnode=   3, nedge=   3, nface=   1)
    executing [ 171] rotatex:       90.00000      0.00000      0.00000
                          Body      6 created  (toler= 1.0000e-07, nnode=   3, nedge=   3, nface=   1)
    executing [ 172] rotatey:       -5.00000      0.00000      0.00000
                          Body      7 created  (toler= 1.0000e-07, nnode=   3, nedge=   3, nface=   1)
    executing [ 173] translate:      1.40965     -3.87298      0.27083
                          Body      8 created  (toler= 1.0000e-07, nnode=   3, nedge=   3, nface=   1)
    executing [ 174] rule:           0.00000      0.00000
                          ruling  2 Xsects with 3 Strips each...
                          Body      9 created  (toler= 1.0000e-07, nnode=   6, nedge=   9, nface=   5)
    executing [ 175] set:            ruledBody  @nbody
                          ruledBody =     9.00000     0.00000
    executing [ 176] select:   face  9  1
                     putting Branch Attributes on Face 4
    executing [ 177] select:   face  9  2
                     putting Branch Attributes on Face 5
    executing [ 178] select:   face  9  3
                     putting Branch Attributes on Face 1
    executing [ 179] select:   face  9  4
                     putting Branch Attributes on Face 2
    executing [ 180] select:   edge  9  3  9  4  1
                     putting Branch Attributes on Edge 3
    executing [ 181] ifthen:             0.00000  EQ      0.00000  and      0.00000  eq      0.00000
    executing [ 182] select:   face  9  5
                     putting Branch Attributes on Face 3
    executing [ 186] store:      LeftWing      0.00000      1.00000
                          Body      9 stored
    executing [ 187] restore:    LeftWing      0.00000
                          Body     10 restored (toler= 1.0000e-07, nnode=   6, nedge=   9, nface=   5)
    executing [ 188] select:   face  tagType  tip  *  *  *  *
                     putting Branch Attributes on Face 5
    executing [ 189] select:   edge  tagType  leadingEdge  *  *  *  *
    executing [ 190] ifthen:             3.00000  GT      0.00000  and      0.00000  eq      0.00000
    executing [ 191] select:   edge  tagType  leadingEdge  *  *  *  *
                     putting Branch Attributes on Edge 3
    executing [ 193] select:   edge  tagType  trailingEdge  *  *  *  *
ERROR:: (edge_not_found) in Branch Brch_000193 at [[../ESP/wing3.csm:103]]
        SELECT specified nonexistant Edge
    executing [ 197] catbeg:         $edge_not_found
    --> catching signal -223 (edge_not_found)
    executing [ 199] mirror:         0.00000      1.00000      0.00000      0.00000
                          Body     11 created  (toler= 1.0000e-07, nnode=   6, nedge=   9, nface=   5)
    executing [ 200] join:           0.00000      0.00000
                          Body     12 created  (toler= 1.0000e-07, nnode=   9, nedge=  15, nface=   8)
    executing [ 201] select:   edge  9  3  9  3  1
                     putting Branch Attributes on Edge 2
    executing [ 202] select:   edge  9  4  9  4  1
                     putting Branch Attributes on Edge 5
    executing [ 203] store:      WingOml      0.00000      0.00000
                          Body     12 stored
    executing [ 205] ifthen:             1.00000  EQ      1.00000  and      0.00000  eq      0.00000
    executing [ 206] restore:    WingOml      0.00000
                          Body     13 restored (toler= 1.0000e-07, nnode=   9, nedge=  15, nface=   8)
    executing [ 207] set:            xmin  @xmin-0.1
                          xmin =    -0.10102     0.00000
    executing [ 208] set:            xmax  @xmax+0.1
                          xmax =     2.47425     0.00000
    executing [ 209] set:            ymin  0
                          ymin =     0.00000     0.00000
    executing [ 210] set:            ymax  @ymax+0.1
                          ymax =     3.97298     0.00000
    executing [ 211] set:            zmin  @zmin-0.1
                          zmin =    -0.13316     0.00000
    executing [ 212] set:            zmax  @zmax+0.1
                          zmax =     0.49998     0.00000
    executing [ 213] store:      .      0.00000      0.00000
                          Body     13 removed from stack
    executing [ 214] udparg:     waffle depth     3.00000 
                          Body     14 created  (NULL Body)
    executing [ 215] udparg:     waffle depth     0.20000 
                          Body     15 created  (NULL Body)
    executing [ 216] udparg:     waffle depth     0.70000 
                          Body     16 created  (NULL Body)
    executing [ 217] udprim:     waffle depth     0.63315 filename tmp_OpenCSM_00/00 (compiled code)
    processing: 
    processing:         # construction lines for spars
    processing:         CPOINT A   AT          0+wing:spar1*wing:chordr 0
    processing:         CPOINT B   AT  wing:xtip+wing:spar1*wing:chordt -wing:ytip
    processing:         CPOINT C   AT          0+wing:spar2*wing:chordr 0
    processing:         CPOINT D   AT  wing:xtip+wing:spar2*wing:chordt -wing:ytip
    processing: 
    processing:         CLINE  AB      A  B
    processing:         CLINE  CD      C  D
    processing: 
    processing:         # rite spars
    processing:         POINT  E   ON  AB   YLOC  ymin
    processing:         POINT  F   ON  AB   YLOC  ymax
    processing:         LINE   EF  E   F  tagComp=riteWing  tagType=spar  tagIndex=1
    processing: 
    processing:         POINT  G   ON  CD   YLOC  ymin
    processing:         POINT  H   ON  CD   YLOC  ymax
    processing:         LINE   GH  G   H  tagComp=riteWing  tagType=spar tagIndex=2
    processing: 
    processing:         # rite ribs
    processing:         PATBEG  irib  wing:nrib
    processing:             CPOINT  I  AT  xmin  -wing:ytip*irib/(wing:nrib+1)
    processing:             CPOINT  J  AT  xmax  y@I
    processing:             LINE    .   I  J  tagComp=riteWing  tagType=rib   tagIndex=!val2str(irib,0)
    processing:         PATEND
    processing:             CPOINT  I  AT  xmin  -wing:ytip*irib/(wing:nrib+1)
    processing:             CPOINT  J  AT  xmax  y@I
    processing:             LINE    .   I  J  tagComp=riteWing  tagType=rib   tagIndex=!val2str(irib,0)
    processing:         PATEND
    processing:             CPOINT  I  AT  xmin  -wing:ytip*irib/(wing:nrib+1)
    processing:             CPOINT  J  AT  xmax  y@I
    processing:             LINE    .   I  J  tagComp=riteWing  tagType=rib   tagIndex=!val2str(irib,0)
    processing:         PATEND
    processing: 
    processing:         # root rib
    processing:         CPOINT  I  AT  xmin  0
    processing:         CPOINT  J  AT  xmax  y@I
    processing:         LINE    .   I  J  tagComp=rootWing  tagType=rib   tagIndex=0
    processing: 
    processing:         # left spars
    processing:         POINT  E   AT  x@E  -y@E
    processing:         POINT  F   AT  x@F  -y@F
    processing:         LINE   FE  F   E  tagComp=leftWing  tagType=spar  tagIndex=1
    processing: 
    processing:         POINT  G   AT  x@G  -y@G
    processing:         POINT  H   AT  x@H  -y@H
    processing:         LINE   HG  H   G  tagComp=leftWing  tagType=spar tagIndex=2
    processing: 
    processing:         # left ribs
    processing:         PATBEG  irib  wing:nrib
    processing:             CPOINT  I  AT  xmin  wing:ytip*irib/(wing:nrib+1)
    processing:             CPOINT  J  AT  xmax  y@I
    processing:             LINE    .   I  J  tagComp=leftWing  tagType=rib   tagIndex=!val2str(irib,0)
    processing:         PATEND
    processing:             CPOINT  I  AT  xmin  wing:ytip*irib/(wing:nrib+1)
    processing:             CPOINT  J  AT  xmax  y@I
    processing:             LINE    .   I  J  tagComp=leftWing  tagType=rib   tagIndex=!val2str(irib,0)
    processing:         PATEND
    processing:             CPOINT  I  AT  xmin  wing:ytip*irib/(wing:nrib+1)
    processing:             CPOINT  J  AT  xmax  y@I
    processing:             LINE    .   I  J  tagComp=leftWing  tagType=rib   tagIndex=!val2str(irib,0)
    processing:         PATEND
                          Body     17 created  (toler= 1.0000e-07, nnode=  64, nedge= 106, nface=  37)
    executing [ 218] translate:      0.00000      0.00000     -0.13316
                          Body     18 created  (toler= 1.0000e-07, nnode=  64, nedge= 106, nface=  37)
    executing [ 219] store:      WingWaffle      0.00000      0.00000
                          Body     18 stored
    executing [ 221] udprim:     $/capsViews (scripted code)
              [ 222] interface:  .  ALL      0.00000
    executing [ 223] ifthen:             0.00000  NE      0.00000  and  ...
    executing [ 268] ifthen:             1.00000  NE      0.00000  and      0.00000  eq      0.00000
    executing [ 269] udprim:     $/viewVLM (scripted code)
              [ 270] interface:  .  ALL      0.00000
    executing [ 271] set:            vlmAIMs  $avlAIM;$astrosAIM;nastranAIM;egadsTessAIM
                          vlmAIMs = $avlAIM;$astrosAIM;nastranAIM;egadsTessAIM
    executing [ 272] ifthen:             1.00000  EQ      1.00000  and      0.00000  eq      0.00000
    executing [ 273] restore:    WingOml      0.00000
                          Body     19 restored (toler= 1.0000e-07, nnode=   9, nedge=  15, nface=   8)
    executing [ 274] set:            xmin  @xmin-1
                          xmin =    -1.00102     0.00000
    executing [ 275] set:            xmax  @xmax+1
                          xmax =     3.37425     0.00000
    executing [ 276] set:            ymin  @ymin+0.001
                          ymin =    -3.87198     0.00000
    executing [ 277] set:            ymax  @ymax-0.001
                          ymax =     3.87198     0.00000
    executing [ 278] set:            zmin  @zmin-1
                          zmin =    -1.03316     0.00000
    executing [ 279] set:            zmax  @zmax+1
                          zmax =     1.39998     0.00000
    executing [ 280] store:      .      0.00000      0.00000
                          Body     19 removed from stack
    executing [ 281] set:            WingVlmNcut  3
                          WingVlmNcut =     3.00000     0.00000
    executing [ 282] mark:
                          Mark        created
    executing [ 283] patbeg:         icut      3.00000
                          pattern counter: icut =   1
    executing [ 284] set:            y  ymin+(ymax-ymin)*(icut-1)/(WingVlmNcut-1)
                          y =    -3.87198     0.00000
    executing [ 285] box:           -1.00102     -3.87198     -1.03316      4.37527      0.00000      2.43315
                          Body     20 created  (toler= 1.0000e-07, nnode=   4, nedge=   4, nface=   1)
    executing [ 286] restore:    WingOml      0.00000
                          Body     21 restored (toler= 1.0000e-07, nnode=   9, nedge=  15, nface=   8)
    executing [ 287] intersect:  none      1.00000   0.0000e+00
                          Body     22 created  (toler= 5.0000e-06, nnode=   3, nedge=   3, nface=   1)
    executing [ 288] select:   face  1
                     putting Branch Attributes on Face 1
    executing [ 289] patend:
                          pattern counter: icut =   2
    executing [ 284] set:            y  ymin+(ymax-ymin)*(icut-1)/(WingVlmNcut-1)
                          y =     0.00000     0.00000
    executing [ 285] box:           -1.00102      0.00000     -1.03316      4.37527      0.00000      2.43315
                          Body     23 created  (toler= 1.0000e-07, nnode=   4, nedge=   4, nface=   1)
    executing [ 286] restore:    WingOml      0.00000
                          Body     24 restored (toler= 1.0000e-07, nnode=   9, nedge=  15, nface=   8)
    executing [ 287] intersect:  none      1.00000   0.0000e+00
                          Body     25 created  (toler= 1.0000e-07, nnode=   3, nedge=   3, nface=   1)
    executing [ 288] select:   face  1
                     putting Branch Attributes on Face 1
    executing [ 289] patend:
                          pattern counter: icut =   3
    executing [ 284] set:            y  ymin+(ymax-ymin)*(icut-1)/(WingVlmNcut-1)
                          y =     3.87198     0.00000
    executing [ 285] box:           -1.00102      3.87198     -1.03316      4.37527      0.00000      2.43315
                          Body     26 created  (toler= 1.0000e-07, nnode=   4, nedge=   4, nface=   1)
    executing [ 286] restore:    WingOml      0.00000
                          Body     27 restored (toler= 1.0000e-07, nnode=   9, nedge=  15, nface=   8)
    executing [ 287] intersect:  none      1.00000   0.0000e+00
                          Body     28 created  (toler= 5.0000e-06, nnode=   3, nedge=   3, nface=   1)
    executing [ 288] select:   face  1
                     putting Branch Attributes on Face 1
    executing [ 289] patend:
    executing [ 290] ifthen:             1.00000  EQ      0.00000  and  ...
    executing [ 299] ifthen:             0.00000  EQ      1.00000  and  ...
    executing [ 321] group:             0.00000
                          Body     25 added to Group   28
                          Body     22 added to Group   28
    executing [ 323] ifthen:             0.00000  EQ      1.00000  and  ...
    executing [ 365] ifthen:             0.00000  EQ      1.00000  and  ...
    executing [ 407] end:
    executing [ 409] ifthen:             0.00000  NE      0.00000  and  ...
    executing [ 852] ifthen:             0.00000  NE      0.00000  and  ...
    executing [1290] ifthen:             1.00000  NE      0.00000  OR  ...
    executing [1291] udprim:     $/viewStructure (scripted code)
              [1292] interface:  .  ALL      0.00000
    executing [1293] set:            structAIMs  $nastranAIM;astrosAIM;mystranAIM;egadsTessAIM
                          structAIMs = $nastranAIM;astrosAIM;mystranAIM;egadsTessAIM
    executing [1294] ifthen:             1.00000  EQ      1.00000  and      0.00000  eq      0.00000
    executing [1295] restore:    WingOml      0.00000
                          Body     29 restored (toler= 1.0000e-07, nnode=   9, nedge=  15, nface=   8)
    executing [1296] restore:    WingWaffle      0.00000
                          Body     30 restored (toler= 1.0000e-07, nnode=  64, nedge= 106, nface=  37)
    executing [1297] intersect:  none      1.00000   0.0000e+00
                          Body     31 created  (toler= 5.0000e-06, nnode=  57, nedge=  99, nface=  37)
    executing [1298] restore:    WingOml      0.00000
                          Body     32 restored (toler= 1.0000e-07, nnode=   9, nedge=  15, nface=   8)
    executing [1299] restore:    WingWaffle      0.00000
                          Body     33 restored (toler= 1.0000e-07, nnode=  64, nedge= 106, nface=  37)
    executing [1300] subtract:   none      1.00000   0.0000e+00
                          Body     34 created  (toler= 6.7429e-07, nnode=  63, nedge= 123, nface=  62)
    executing [1301] extract:    0
                          Body     35 created  (toler= 6.7429e-07, nnode=  63, nedge= 123, nface=  62)
    executing [1302] union:          0.00000  0   0.0000e+00
                          Body     36 created  (toler= 5.0000e-06, nnode=  63, nedge= 137, nface=  99)
    executing [1303] ifthen:             0.00000  EQ      1.00000  and  ...
    executing [1306] else:
    executing [1307] udprim:     editAttr filename tmp_OpenCSM_00/05 (compiled code)
    processing:             FACE HAS        tagComp=leftWing

    processing:             SET             capsGroup=leftWingSkin

    processing:     

    processing:             FACE HAS        tagComp=riteWing

    processing:             SET             capsGroup=riteWingSkin

    processing:     

    processing:             FACE HAS        tagType=tip

    processing:             SET             capsGroup=wingRib

    processing:     

    processing:             FACE HAS        tagType=trailingEdge

    processing:             SET             capsGroup=wingTE

    processing:     

    processing:             FACE HAS        tagType=rib

    processing:             SET             capsGroup=wingRib

    processing: 

    processing:             FACE HAS        tagType=spar tagIndex=1

    processing:             SET             capsGroup=wingSpar1

    processing:             SET             capsMesh=wingSpar1

    processing: 

    processing:             FACE HAS        tagType=spar tagIndex=2

    processing:             SET             capsGroup=wingSpar2

    processing:             SET             capsMesh=wingSpar2

WARNING:: toler =   5.0000e-06 for UDPRIM
                          Body     37 created  (toler= 5.0000e-06, nnode=  63, nedge= 137, nface=  99)
    executing [1309] udprim:     editAttr filename tmp_OpenCSM_00/06 (compiled code)
    processing:         FACE HAS      tagType=upper

    processing:         SET           capsBound=upperWing

    processing: 

    processing:         FACE HAS      tagType=lower

    processing:         SET           capsBound=lowerWing

    processing: 

    processing:         FACE HAS      tagType=tip tagIndex=1

    processing:         SET           capsBound=leftTip

    processing: 

    processing:         FACE HAS      tagType=tip tagIndex=2

    processing:         SET           capsBound=riteTip

WARNING:: toler =   5.0000e-06 for UDPRIM
                          Body     38 created  (toler= 5.0000e-06, nnode=  63, nedge= 137, nface=  99)
    executing [1310] udprim:     editAttr filename tmp_OpenCSM_00/07 (compiled code)
    processing:         NODE ADJ2FACE tagComp=leftWing tagType=tip

    processing:         AND  ADJ2FACE tagType=lower

    processing:         AND  ADJ2FACE tagType=spar tagIndex=1

    processing:         SET           capsLoad=leftPointLoad

    processing: 

    processing:         NODE ADJ2FACE tagComp=riteWing tagType=tip

    processing:         AND  ADJ2FACE tagType=lower

    processing:         AND  ADJ2FACE tagType=spar tagIndex=1

    processing:         SET           capsLoad=ritePointLoad

WARNING:: toler =   5.0000e-06 for UDPRIM
                          Body     39 created  (toler= 5.0000e-06, nnode=  63, nedge= 137, nface=  99)
    executing [1311] select:   edge  tagType  leadingEdge  *  *  *  *
    executing [1312] dimension:     leadingEdges      1.00000      8.00000
    executing [1313] set:            leadingEdges  @sellist
                          leadingEdges[1,1] =     8.00000     0.00000
                          leadingEdges[1,2] =    31.00000     0.00000
                          leadingEdges[1,3] =    33.00000     0.00000
                          leadingEdges[1,4] =    62.00000     0.00000
                          leadingEdges[1,5] =    64.00000     0.00000
                          leadingEdges[1,6] =    94.00000     0.00000
                          leadingEdges[1,7] =    96.00000     0.00000
                          leadingEdges[1,8] =   121.00000     0.00000
    executing [1314] patbeg:         i      8.00000
                          pattern counter: i =   1
    executing [1315] select:   edge  8
                     putting Branch Attributes on Edge 8
    executing [1316] patend:
                          pattern counter: i =   2
    executing [1315] select:   edge  31
                     putting Branch Attributes on Edge 31
    executing [1316] patend:
                          pattern counter: i =   3
    executing [1315] select:   edge  33
                     putting Branch Attributes on Edge 33
    executing [1316] patend:
                          pattern counter: i =   4
    executing [1315] select:   edge  62
                     putting Branch Attributes on Edge 62
    executing [1316] patend:
                          pattern counter: i =   5
    executing [1315] select:   edge  64
                     putting Branch Attributes on Edge 64
    executing [1316] patend:
                          pattern counter: i =   6
    executing [1315] select:   edge  94
                     putting Branch Attributes on Edge 94
    executing [1316] patend:
                          pattern counter: i =   7
    executing [1315] select:   edge  96
                     putting Branch Attributes on Edge 96
    executing [1316] patend:
                          pattern counter: i =   8
    executing [1315] select:   edge  121
                     putting Branch Attributes on Edge 121
    executing [1316] patend:
    executing [1317] udprim:     editAttr filename tmp_OpenCSM_00/08 (compiled code)
    processing:         FACE ADJ2EDGE tagComp=leftWing

    processing:         SET           tagTemp=leadingEdgeFace

WARNING:: toler =   5.0000e-06 for UDPRIM
                          Body     40 created  (toler= 5.0000e-06, nnode=  63, nedge= 137, nface=  99)
    executing [1318] udprim:     editAttr filename tmp_OpenCSM_00/09 (compiled code)
    processing:         EDGE ADJ2FACE tagTemp=leadingEdgeFace

    processing:         AND  ADJ2FACE tagComp=rootWing

    processing:         SET           capsMesh=rootLeadingEdge

WARNING:: toler =   5.0000e-06 for UDPRIM
                          Body     41 created  (toler= 5.0000e-06, nnode=  63, nedge= 137, nface=  99)
    executing [1319] ifthen:             1.00000  EQ      1.00000  and      0.00000  eq      0.00000
    executing [1320] udprim:     editAttr filename tmp_OpenCSM_00/10 (compiled code)
    processing:             FACE HAS      tagComp=rootWing

    processing:             SET           capsConstraint=rootConstraint

    processing:        

    processing:             EDGE ADJ2FACE tagComp=rootWing

    processing:             SET  capsConstraint=rootConstraint

    processing:     

    processing:             NODE ADJ2FACE tagComp=rootWing

    processing:             SET  capsConstraint=rootConstraint

WARNING:: toler =   5.0000e-06 for UDPRIM
                          Body     42 created  (toler= 5.0000e-06, nnode=  63, nedge= 137, nface=  99)
    executing [1322] ifthen:             0.00000  EQ      1.00000  and  ...
    executing [1325] udprim:     editAttr filename tmp_OpenCSM_00/12 (compiled code)
    processing:         FACE HAS      tagComp=leftWing tagType=upper

    processing:         AND  ADJ2EDGE tagType=leadingEdge

    processing:         AND  ADJ2FACE tagComp=riteWing

    processing:         SET           tagCsys=leftWing

    processing: 

    processing:         FACE HAS      tagComp=riteWing tagType=upper

    processing:         AND  ADJ2EDGE tagType=leadingEdge

    processing:         AND  ADJ2FACE tagComp=leftWing

    processing:         SET           tagCsys=riteWing

WARNING:: toler =   5.0000e-06 for UDPRIM
                          Body     43 created  (toler= 5.0000e-06, nnode=  63, nedge= 137, nface=  99)
    executing [1326] select:   face  tagCsys  leftWing  *  *  *  *
    executing [1327] set:            leftWingSkinCsys  @sellist
                          leftWingSkinCsys =    27.00000     0.00000
    executing [1328] select:   face  tagCsys  riteWing  *  *  *  *
    executing [1329] set:            riteWingSkinCsys  @sellist
                          riteWingSkinCsys =     8.00000     0.00000
    executing [1330] store:      WingStruct      0.00000      0.00000
                          Body     43 stored
    executing [1331] restore:    WingStruct      0.00000
                          Body     44 restored (toler= 5.0000e-06, nnode=  63, nedge= 137, nface=  99)
    executing [1332] store:      WingStruct      0.00000      0.00000
WARNING:: storage WingStruct (0) is being overwritten
                          Body     44 stored
    executing [1334] restore:    WingStruct      0.00000
                          Body     45 restored (toler= 5.0000e-06, nnode=  63, nedge= 137, nface=  99)
    executing [1335] select:   body
                    putting Branch Attributes on Body
    executing [1336] ifthen:             0.00000  EQ      1.00000  and  ...
    executing [1339] end:
    executing [1341] ifthen:             0.00000  NE      0.00000  and  ...
    executing [1378] end:
    finalizing:
==> Profile information
    Branch type           ncall  time (sec)    pct
    dimension                 1       0.000    0.0
    box                       3       0.004    0.0
    udprim                   14       0.625    1.5
    restore                  12       0.050    0.1
    rule                      1       0.095    0.2
    intersect                 4       4.870   11.9
    subtract                  1       4.816   11.8
    union                     1      29.261   71.6
    join                      1       0.139    0.3
    extract                   1       0.851    2.1
    translate                 2       0.024    0.1
    rotatex                   2       0.003    0.0
    rotatey                   1       0.002    0.0
    scale                     2       0.003    0.0
    mirror                    1       0.036    0.1
    interface                 4       0.000    0.0
    end                       4       0.000    0.0
    set                      77       0.001    0.0
    udparg                    3       0.000    0.0
    select                   26       0.069    0.2
    store                     7       0.000    0.0
    patbeg                    2       0.000    0.0
    patend                   11       0.000    0.0
    ifthen                   48       0.001    0.0
    else                      2       0.000    0.0
    endif                    48       0.000    0.0
    catbeg                    1       0.000    0.0
    catend                    1       0.000    0.0
    mark                      2       0.000    0.0
    group                     1       0.000    0.0
    Total                   284      40.850
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 7
	Name = Wing, index = 1
	Name = wingSpar1, index = 2
	Name = riteWingSkin, index = 3
	Name = wingRib, index = 4
	Name = leftWingSkin, index = 5
	Name = wingSpar2, index = 6
	Name = wingTE, index = 7
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar1, index = 1
	Name = wingSpar2, index = 2
	Name = leadingEdge, index = 3
	Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 4)
	Tessellating body
Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value
Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value
Warning: No capsGroup/capsIgnore attribute found on edge 3 of face 1, unable to assign a boundary index value
Number of nodes = 7
Number of elements = 3
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 0
Number of quadrilateral elements = 3
Getting surface mesh for body 2 (of 4)
	Tessellating body
Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value
Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value
Warning: No capsGroup/capsIgnore attribute found on edge 3 of face 1, unable to assign a boundary index value
Number of nodes = 7
Number of elements = 3
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 0
Number of quadrilateral elements = 3
Getting surface mesh for body 3 (of 4)
	Tessellating body
Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value
Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value
Warning: No capsGroup/capsIgnore attribute found on edge 3 of face 1, unable to assign a boundary index value
Number of nodes = 7
Number of elements = 3
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 0
Number of quadrilateral elements = 3
Getting surface mesh for body 4 (of 4)
	Tessellating body
Number of nodes = 299
Number of elements = 387
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 0
Number of quadrilateral elements = 387
----------------------------
Total number of nodes = 320
Total number of elements = 396
Analysis directory does not currently exist - it will be made automatically
 CAPS Info: No symbol for aimExecute in nastranAIM
 CAPS Info: No symbol for aimCheck in nastranAIM
 CAPS Info: No symbol for aimSensitivity in nastranAIM

==> Running Nastran pre-analysis...
Mapping Csys attributes ................
	Number of unique Csys attributes = 2
	Name = leftWingSkin, index = 1
	Name = riteWingSkin, index = 2

Getting FEA coordinate systems.......
	Number of coordinate systems - 2
	Coordinate system name - leftWingSkin
	Coordinate system name - riteWingSkin
Mapping capsConstraint attributes ................
	Number of unique capsConstraint attributes = 1
	Name = rootConstraint, index = 1
Mapping capsLoad attributes ................
	Number of unique capsLoad attributes = 2
	Name = ritePointLoad, index = 1
	Name = leftPointLoad, index = 2
Mapping capsBound attributes ................
	Number of unique capsBound attributes = 4
	Name = lowerWing, index = 1
	Name = upperWing, index = 2
	Name = riteTip, index = 3
	Name = leftTip, index = 4
Mapping capsConnect attributes ................
	Number of unique capsConnect attributes = 0
Mapping capsResponse attributes ................
	Number of unique capsResponse attributes = 0
Found link for attrMap (Attribute_Map) from parent
Found link for a Surface mesh from parent
Setting FEA Data
	Mesh for body = 0
	Number of nodal coordinates = 7
	Number of elements = 3
	Elemental Nodes = 0
	Elemental Rods  = 0
	Elemental Tria3 = 0
	Elemental Quad4 = 3
Setting FEA Data
	Mesh for body = 1
	Number of nodal coordinates = 7
	Number of elements = 3
	Elemental Nodes = 0
	Elemental Rods  = 0
	Elemental Tria3 = 0
	Elemental Quad4 = 3
Setting FEA Data
	Mesh for body = 2
	Number of nodal coordinates = 7
	Number of elements = 3
	Elemental Nodes = 0
	Elemental Rods  = 0
	Elemental Tria3 = 0
	Elemental Quad4 = 3
Setting FEA Data
	Mesh for body = 3
	Number of nodal coordinates = 299
	Number of elements = 387
	Elemental Nodes = 0
	Elemental Rods  = 0
	Elemental Tria3 = 0
	Elemental Quad4 = 387
Combining multiple FEA meshes!
	Combined Number of nodal coordinates = 320
	Combined Number of elements = 396
	Combined Elemental Nodes = 0
	Combined Elemental Rods  = 0
	Combined Elemental Tria3 = 0
	Combined Elemental Quad4 = 396
Getting vortex lattice surface data
	VLM surface name - upperWing
	Done getting vortex lattice surface data

Getting FEA vortex lattice mesh
	Surface 1: Number of points found for aero-spline = 12
	Surface 2: Number of points found for aero-spline = 12

Getting FEA materials.......
	Number of materials - 2
	Material name - Unobtainium
	No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic"
	Material name - Madeupium
	Done getting FEA materials

Getting FEA properties.......
	Number of properties - 5
	Property name - leftWingSkin
	Property name - riteWingSkin
	Property name - wingRib
	Property name - wingSpar1
	Property name - wingSpar2
	Done getting FEA properties
Updating mesh element types based on properties input

Getting FEA constraints.......
	Number of constraints - 1
	Constraint name - rootConstraint
	No "constraintType" specified for Constraint tuple rootConstraint, defaulting to "ZeroDisplacement"
	Done getting FEA constraints
Support tuple is NULL - No supports applied
Connect tuple is NULL - Using defaults
Load tuple is NULL - No loads applied
Design_Variable tuple is NULL - No design variables applied
Design_Constraint tuple is NULL - No design constraints applied
Design_Equation tuple is NULL - No design equations applied
Design_Table tuple is NULL - No design table constants applied
Design_Opt_Param tuple is NULL - No design optimization parameters applied
Design_Response tuple is NULL - No design responses applied
Design_Equation_Response tuple is NULL - No design equation responses applied

Getting FEA analyses.......
	Number of analyses - 1
	Analysis name - Flutter
	Done getting FEA analyses

Writing Nastran grid and connectivity file (in large field format) ....
Finished writing Nastran grid file

Writing subElement types (if any) - appending mesh file

Writing Nastran instruction file....
SUBCASE = 0
	Warning: No loads specified for case Flutter!!!!
	Writing aero card
	Writing analysis cards
	Writing constraint ADD cards
	Writing constraint cards
	Writing material cards
	Writing property cards
	Writing coordinate system cards
	Writing aeroelastic cards

==> Running Nastran...
sh: nastran: command not found
--> temporary directory "tmp_OpenCSM_00" removed
 Cleaning up egadsInstance - 0
 Cleaning up nastranInstance - 0
 EGADS Info: 906 Objects, 1436 Reference in Use (of 33673) at Close!

real	0m17.733s
user	0m37.461s
sys	0m4.650s
+ status=0
+ set +x

=================================================
data/session10/nastran_5_Flutter.py passed (as expected)
=================================================


=================================================
aeroelastic_Iterative_SU2_Astros.py test;
+ python aeroelastic_Iterative_SU2_Astros.py
+ tee -a /Users/jenkins/workspace/ESP_QuickTestCaps/7.4/CAPS/training/DARWIN64/CAPS/training/training.log
Definition of "kt" in "/Users/jenkins/workspace/ESP_QuickTestCaps/7.4/CAPS/training/DARWIN64/ESP/udunits/udunits2-common.xml", line 90, overrides prefixed-unit "1000000 kilogram"
Definition of "microns" in "/Users/jenkins/workspace/ESP_QuickTestCaps/7.4/CAPS/training/DARWIN64/ESP/udunits/udunits2-common.xml", line 336, overrides prefixed-unit "1e-15 second"
Definition of "ft" in "/Users/jenkins/workspace/ESP_QuickTestCaps/7.4/CAPS/training/DARWIN64/ESP/udunits/udunits2-common.xml", line 433, overrides prefixed-unit "1e-12 kilogram"
Definition of "yd" in "/Users/jenkins/workspace/ESP_QuickTestCaps/7.4/CAPS/training/DARWIN64/ESP/udunits/udunits2-common.xml", line 441, overrides prefixed-unit "8.64e-20 second"
Definition of "pt" in "/Users/jenkins/workspace/ESP_QuickTestCaps/7.4/CAPS/training/DARWIN64/ESP/udunits/udunits2-common.xml", line 655, overrides prefixed-unit "1e-09 kilogram"
Definition of "at" in "/Users/jenkins/workspace/ESP_QuickTestCaps/7.4/CAPS/training/DARWIN64/ESP/udunits/udunits2-common.xml", line 1052, overrides prefixed-unit "1e-15 kilogram"
Definition of "ph" in "/Users/jenkins/workspace/ESP_QuickTestCaps/7.4/CAPS/training/DARWIN64/ESP/udunits/udunits2-common.xml", line 1571, overrides prefixed-unit "3.6e-09 second"
Definition of "nt" in "/Users/jenkins/workspace/ESP_QuickTestCaps/7.4/CAPS/training/DARWIN64/ESP/udunits/udunits2-common.xml", line 1578, overrides prefixed-unit "1e-06 kilogram"
--> enter ocsmCheck()
--> checks passed
--> enter ocsmSave(filename=capsTmp.cpc)
--> enter ocsmCheck()
--> checks passed
Analysis directory does not currently exist - it will be made automatically
 CAPS Info: No symbol for aimDiscr in aflr4AIM
 CAPS Info: No symbol for aimFreeDiscr in aflr4AIM
 CAPS Info: No symbol for aimLocateElement in aflr4AIM
 CAPS Info: No symbol for aimUsesDataSet in aflr4AIM
 CAPS Info: No symbol for aimCheck in aflr4AIM
 CAPS Info: No symbol for aimTransfer in aflr4AIM
 CAPS Info: No symbol for aimInterpolation in aflr4AIM
 CAPS Info: No symbol for aimInterpolateBar in aflr4AIM
 CAPS Info: No symbol for aimIntegration in aflr4AIM
 CAPS Info: No symbol for aimIntegrateBar in aflr4AIM
 CAPS Info: No symbol for aimSensitivity in aflr4AIM
Analysis directory does not currently exist - it will be made automatically
 CAPS Info: No symbol for aimDiscr in aflr3AIM
 CAPS Info: No symbol for aimFreeDiscr in aflr3AIM
 CAPS Info: No symbol for aimLocateElement in aflr3AIM
 CAPS Info: No symbol for aimUsesDataSet in aflr3AIM
 CAPS Info: No symbol for aimCheck in aflr3AIM
 CAPS Info: No symbol for aimTransfer in aflr3AIM
 CAPS Info: No symbol for aimInterpolation in aflr3AIM
 CAPS Info: No symbol for aimInterpolateBar in aflr3AIM
 CAPS Info: No symbol for aimIntegration in aflr3AIM
 CAPS Info: No symbol for aimIntegrateBar in aflr3AIM
 CAPS Info: No symbol for aimSensitivity in aflr3AIM
Analysis directory does not currently exist - it will be made automatically
 CAPS Info: No symbol for aimExecute in su2AIM
 CAPS Info: No symbol for aimCheck in su2AIM
 CAPS Info: No symbol for aimData in su2AIM
 CAPS Info: No symbol for aimSensitivity in su2AIM
Analysis directory does not currently exist - it will be made automatically
 CAPS Info: No symbol for aimDiscr in egadsTessAIM
 CAPS Info: No symbol for aimFreeDiscr in egadsTessAIM
 CAPS Info: No symbol for aimLocateElement in egadsTessAIM
 CAPS Info: No symbol for aimUsesDataSet in egadsTessAIM
 CAPS Info: No symbol for aimCheck in egadsTessAIM
 CAPS Info: No symbol for aimTransfer in egadsTessAIM
 CAPS Info: No symbol for aimInterpolation in egadsTessAIM
 CAPS Info: No symbol for aimInterpolateBar in egadsTessAIM
 CAPS Info: No symbol for aimIntegration in egadsTessAIM
 CAPS Info: No symbol for aimIntegrateBar in egadsTessAIM
 CAPS Info: No symbol for aimSensitivity in egadsTessAIM
Analysis directory does not currently exist - it will be made automatically
 CAPS Info: No symbol for aimExecute in astrosAIM
 CAPS Info: No symbol for aimCheck in astrosAIM
 CAPS Info: No symbol for aimData in astrosAIM
 CAPS Info: No symbol for aimSensitivity in astrosAIM
--> enter ocsmBuild(buildTo=0)
--> enter ocsmCheck()
--> checks passed

    Interim EGADS version  1.19 (with  OpenCASCADE 7.4.1)

    executing [   1] udprim:     $/capsHeader (scripted code)
              [   2] interface:  .  ALL      0.00000
    executing [   3] set:            makeFuseOml  0
                          makeFuseOml =     0.00000     0.00000
    executing [   4] set:            makeFuseWaffle  0
                          makeFuseWaffle =     0.00000     0.00000
    executing [   5] set:            makeFuseCmass  0
                          makeFuseCmass =     0.00000     0.00000
    executing [   6] set:            makeWingOml  0
                          makeWingOml =     0.00000     0.00000
    executing [   7] set:            makeWingHinge  0
                          makeWingHinge =     0.00000     0.00000
    executing [   8] set:            makeWingWaffle  0
                          makeWingWaffle =     0.00000     0.00000
    executing [   9] set:            makeWingCmass  0
                          makeWingCmass =     0.00000     0.00000
    executing [  10] set:            makeHtailOml  0
                          makeHtailOml =     0.00000     0.00000
    executing [  11] set:            makeHtailHinge  0
                          makeHtailHinge =     0.00000     0.00000
    executing [  12] set:            makeHtailWaffle  0
                          makeHtailWaffle =     0.00000     0.00000
    executing [  13] set:            makeHtailCmass  0
                          makeHtailCmass =     0.00000     0.00000
    executing [  14] set:            makeVtailOml  0
                          makeVtailOml =     0.00000     0.00000
    executing [  15] set:            makeVtailHinge  0
                          makeVtailHinge =     0.00000     0.00000
    executing [  16] set:            makeVtailWaffle  0
                          makeVtailWaffle =     0.00000     0.00000
    executing [  17] set:            makeVtailCmass  0
                          makeVtailCmass =     0.00000     0.00000
    executing [  18] set:            makePylonOml  0
                          makePylonOml =     0.00000     0.00000
    executing [  19] set:            makePodOml  0
                          makePodOml =     0.00000     0.00000
    executing [  20] set:            SHARP_TE  0
                          SHARP_TE =     0.00000     0.00000
    executing [  21] ifthen:             0.00000  EQ      1.00000  and  ...
    executing [  24] ifthen:             0.00000  NE      0.00000  and  ...
    executing [  40] ifthen:             0.00000  EQ      1.00000  and  ...
    executing [  43] ifthen:             0.00000  NE      0.00000  and  ...
    executing [  51] ifthen:             0.00000  EQ      1.00000  and  ...
    executing [  54] ifthen:             1.00000  NE      0.00000  and      0.00000  eq      0.00000
    executing [  55] set:            makeFuseOml  1
                          makeFuseOml =     1.00000     0.00000
    executing [  56] set:            makeWingOml  1
                          makeWingOml =     1.00000     0.00000
    executing [  57] set:            makeWingHinge  1
                          makeWingHinge =     1.00000     0.00000
    executing [  58] set:            makeHtailOml  1
                          makeHtailOml =     1.00000     0.00000
    executing [  59] set:            makeHtailHinge  1
                          makeHtailHinge =     1.00000     0.00000
    executing [  60] set:            makeVtailOml  1
                          makeVtailOml =     1.00000     0.00000
    executing [  61] set:            makeVtailHinge  1
                          makeVtailHinge =     1.00000     0.00000
    executing [  62] set:            makePodOml  1
                          makePodOml =     1.00000     0.00000
    executing [  63] set:            SHARP_TE  1
                          SHARP_TE =     1.00000     0.00000
    executing [  65] ifthen:             0.00000  EQ      1.00000  and  ...
    executing [  68] ifthen:             0.00000  NE      0.00000  and  ...
    executing [  79] ifthen:             0.00000  EQ      1.00000  and  ...
    executing [  82] ifthen:             0.00000  EQ      1.00000  and  ...
    executing [  85] ifthen:             0.00000  EQ      1.00000  and  ...
    executing [  88] ifthen:             1.00000  NE      0.00000  OR  ...
    executing [  89] set:            makeWingOml  1
                          makeWingOml =     1.00000     0.00000
    executing [  90] set:            makeWingWaffle  1
                          makeWingWaffle =     1.00000     0.00000
    executing [  92] ifthen:             0.00000  EQ      1.00000  and  ...
    executing [  95] ifthen:             0.00000  NE      0.00000  and  ...
    executing [ 101] ifthen:             1.00000  EQ      1.00000  and      0.00000  eq      0.00000
    executing [ 102] set:            COMP:Fuse  0
                          COMP:Fuse =     0.00000     0.00000
    executing [ 104] ifthen:             0.00000  EQ      1.00000  and  ...
    executing [ 107] ifthen:             1.00000  EQ      1.00000  and      0.00000  eq      0.00000
    executing [ 108] set:            COMP:Htail  0
                          COMP:Htail =     0.00000     0.00000
    executing [ 110] ifthen:             1.00000  EQ      1.00000  and      0.00000  eq      0.00000
    executing [ 111] set:            COMP:Vtail  0
                          COMP:Vtail =     0.00000     0.00000
    executing [ 113] ifthen:             1.00000  EQ      1.00000  and      0.00000  eq      0.00000
    executing [ 114] set:            COMP:Pylon  0
                          COMP:Pylon =     0.00000     0.00000
    executing [ 116] ifthen:             1.00000  EQ      1.00000  and      0.00000  eq      0.00000
    executing [ 117] set:            COMP:Pod  0
                          COMP:Pod =     0.00000     0.00000
    executing [ 119] ifthen:             1.00000  EQ      1.00000  and      0.00000  eq      0.00000
    executing [ 120] set:            COMP:Control  0
                          COMP:Control =     0.00000     0.00000
    executing [ 122] ifthen:             0.00000  EQ      0.00000  and      0.00000  eq      0.00000
    executing [ 123] set:            makeFuseOml  0
                          makeFuseOml =     0.00000     0.00000
    executing [ 124] set:            makeFuseWaffle  0
                          makeFuseWaffle =     0.00000     0.00000
    executing [ 125] set:            makeFuseCmass  0
                          makeFuseCmass =     0.00000     0.00000
    executing [ 127] ifthen:             1.00000  EQ      0.00000  and  ...
    executing [ 133] ifthen:             0.00000  EQ      0.00000  and      0.00000  eq      0.00000
    executing [ 134] set:            makeHtailOml  0
                          makeHtailOml =     0.00000     0.00000
    executing [ 135] set:            makeHtailHinge  0
                          makeHtailHinge =     0.00000     0.00000
    executing [ 136] set:            makeHtailWaffle  0
                          makeHtailWaffle =     0.00000     0.00000
    executing [ 137] set:            makeHtailCmass  0
                          makeHtailCmass =     0.00000     0.00000
    executing [ 139] ifthen:             0.00000  EQ      0.00000  and      0.00000  eq      0.00000
    executing [ 140] set:            makeVtailOml  0
                          makeVtailOml =     0.00000     0.00000
    executing [ 141] set:            makeVtailHinge  0
                          makeVtailHinge =     0.00000     0.00000
    executing [ 142] set:            makeVtailWaffle  0
                          makeVtailWaffle =     0.00000     0.00000
    executing [ 143] set:            makeVtailCmass  0
                          makeVtailCmass =     0.00000     0.00000
    executing [ 145] ifthen:             0.00000  EQ      0.00000  and      0.00000  eq      0.00000
    executing [ 146] set:            makePylonOml  0
                          makePylonOml =     0.00000     0.00000
    executing [ 148] ifthen:             0.00000  EQ      0.00000  and      0.00000  eq      0.00000
    executing [ 149] set:            makePodOml  0
                          makePodOml =     0.00000     0.00000
    executing [ 151] ifthen:             0.00000  EQ      0.00000  and      0.00000  eq      0.00000
    executing [ 152] set:            makeWingHinge  0
                          makeWingHinge =     0.00000     0.00000
    executing [ 153] set:            makeHtailHinge  0
                          makeHtailHinge =     0.00000     0.00000
    executing [ 154] set:            makeVtailHinge  0
                          makeVtailHinge =     0.00000     0.00000
    executing [ 156] end:
    executing [ 157] set:            wing:span  sqrt(wing:aspect*wing:area)
                          wing:span =     7.74597     0.00000
    executing [ 158] set:            wing:chordr  2*wing:area/wing:span/(1+wing:taper)
                          wing:chordr =     1.61374     0.00000
    executing [ 159] set:            wing:chordt  wing:chordr*wing:taper
                          wing:chordt =     0.96825     0.00000
    executing [ 160] set:            wing:ytip  -wing:span/2
                          wing:ytip =    -3.87298     0.00000
    executing [ 161] set:            wing:xtip  -wing:ytip*tand(wing:sweep)
                          wing:xtip =     1.40965     0.00000
    executing [ 162] set:            wing:ztip  -wing:ytip*tand(wing:dihedral)
                          wing:ztip =     0.27083     0.00000
    executing [ 163] set:            wing:mac  sqrt(wing:area/wing:aspect)
                          wing:mac =     1.29099     0.00000
    executing [ 164] ifthen:             1.00000  EQ      1.00000  and      0.00000  eq      0.00000
    executing [ 165] mark:
                          Mark        created
    executing [ 166] udprim:     naca thickness     0.12000 camber     0.06000 sharpte     1.00000 (compiled code)
                          Body      1 created  (toler= 1.0000e-07, nnode=   2, nedge=   2, nface=   1)
    executing [ 167] scale:          1.61374      0.00000      0.00000      0.00000
                          Body      2 created  (toler= 1.6137e-07, nnode=   2, nedge=   2, nface=   1)
    executing [ 168] rotatex:       90.00000      0.00000      0.00000
                          Body      3 created  (toler= 1.6137e-07, nnode=   2, nedge=   2, nface=   1)
    executing [ 169] udprim:     naca thickness     0.16000 camber     0.02000 sharpte     1.00000 (compiled code)
                          Body      4 created  (toler= 1.0000e-07, nnode=   2, nedge=   2, nface=   1)
    executing [ 170] scale:          0.96825      0.00000      0.00000      0.00000
                          Body      5 created  (toler= 1.0000e-07, nnode=   2, nedge=   2, nface=   1)
    executing [ 171] rotatex:       90.00000      0.00000      0.00000
                          Body      6 created  (toler= 1.0000e-07, nnode=   2, nedge=   2, nface=   1)
    executing [ 172] rotatey:       -5.00000      0.00000      0.00000
                          Body      7 created  (toler= 1.0000e-07, nnode=   2, nedge=   2, nface=   1)
    executing [ 173] translate:      1.40965     -3.87298      0.27083
                          Body      8 created  (toler= 1.0000e-07, nnode=   2, nedge=   2, nface=   1)
    executing [ 174] rule:           0.00000      0.00000
                          ruling  2 Xsects with 2 Strips each...
                          Body      9 created  (toler= 1.0000e-07, nnode=   4, nedge=   6, nface=   4)
    executing [ 175] set:            ruledBody  @nbody
                          ruledBody =     9.00000     0.00000
    executing [ 176] select:   face  9  1
                     putting Branch Attributes on Face 3
    executing [ 177] select:   face  9  2
                     putting Branch Attributes on Face 4
    executing [ 178] select:   face  9  3
                     putting Branch Attributes on Face 1
    executing [ 179] select:   face  9  4
                     putting Branch Attributes on Face 2
    executing [ 180] select:   edge  9  3  9  4  1
                     putting Branch Attributes on Edge 3
    executing [ 181] ifthen:             1.00000  EQ      0.00000  and  ...
    executing [ 183] else:
    executing [ 184] select:   edge  9  3  9  4  2
                     putting Branch Attributes on Edge 1
    executing [ 186] store:      LeftWing      0.00000      1.00000
                          Body      9 stored
    executing [ 187] restore:    LeftWing      0.00000
                          Body     10 restored (toler= 1.0000e-07, nnode=   4, nedge=   6, nface=   4)
    executing [ 188] select:   face  tagType  tip  *  *  *  *
                     putting Branch Attributes on Face 4
    executing [ 189] select:   edge  tagType  leadingEdge  *  *  *  *
    executing [ 190] ifthen:             3.00000  GT      0.00000  and      0.00000  eq      0.00000
    executing [ 191] select:   edge  tagType  leadingEdge  *  *  *  *
                     putting Branch Attributes on Edge 3
    executing [ 193] select:   edge  tagType  trailingEdge  *  *  *  *
    executing [ 194] ifthen:             1.00000  GT      0.00000  and      0.00000  eq      0.00000
    executing [ 195] select:   edge  tagType  trailingEdge  *  *  *  *
                     putting Branch Attributes on Edge 1
    executing [ 197] catbeg:         $edge_not_found
    executing [ 199] mirror:         0.00000      1.00000      0.00000      0.00000
                          Body     11 created  (toler= 1.0000e-07, nnode=   4, nedge=   6, nface=   4)
    executing [ 200] join:           0.00000      0.00000
                          Body     12 created  (toler= 1.0000e-07, nnode=   6, nedge=  10, nface=   6)
    executing [ 201] select:   edge  9  3  9  3  1
                     putting Branch Attributes on Edge 2
    executing [ 202] select:   edge  9  4  9  4  1
                     putting Branch Attributes on Edge 5
    executing [ 203] store:      WingOml      0.00000      0.00000
                          Body     12 stored
    executing [ 205] ifthen:             1.00000  EQ      1.00000  and      0.00000  eq      0.00000
    executing [ 206] restore:    WingOml      0.00000
                          Body     13 restored (toler= 1.0000e-07, nnode=   6, nedge=  10, nface=   6)
    executing [ 207] set:            xmin  @xmin-0.1
                          xmin =    -0.10102     0.00000
    executing [ 208] set:            xmax  @xmax+0.1
                          xmax =     2.47421     0.00000
    executing [ 209] set:            ymin  0
                          ymin =     0.00000     0.00000
    executing [ 210] set:            ymax  @ymax+0.1
                          ymax =     3.97298     0.00000
    executing [ 211] set:            zmin  @zmin-0.1
                          zmin =    -0.13316     0.00000
    executing [ 212] set:            zmax  @zmax+0.1
                          zmax =     0.49990     0.00000
    executing [ 213] store:      .      0.00000      0.00000
                          Body     13 removed from stack
    executing [ 214] udparg:     waffle depth     3.00000 
                          Body     14 created  (NULL Body)
    executing [ 215] udparg:     waffle depth     0.20000 
                          Body     15 created  (NULL Body)
    executing [ 216] udparg:     waffle depth     0.70000 
                          Body     16 created  (NULL Body)
    executing [ 217] udprim:     waffle depth     0.63306 filename tmp_OpenCSM_00/00 (compiled code)
    processing: 
    processing:         # construction lines for spars
    processing:         CPOINT A   AT          0+wing:spar1*wing:chordr 0
    processing:         CPOINT B   AT  wing:xtip+wing:spar1*wing:chordt -wing:ytip
    processing:         CPOINT C   AT          0+wing:spar2*wing:chordr 0
    processing:         CPOINT D   AT  wing:xtip+wing:spar2*wing:chordt -wing:ytip
    processing: 
    processing:         CLINE  AB      A  B
    processing:         CLINE  CD      C  D
    processing: 
    processing:         # rite spars
    processing:         POINT  E   ON  AB   YLOC  ymin
    processing:         POINT  F   ON  AB   YLOC  ymax
    processing:         LINE   EF  E   F  tagComp=riteWing  tagType=spar  tagIndex=1
    processing: 
    processing:         POINT  G   ON  CD   YLOC  ymin
    processing:         POINT  H   ON  CD   YLOC  ymax
    processing:         LINE   GH  G   H  tagComp=riteWing  tagType=spar tagIndex=2
    processing: 
    processing:         # rite ribs
    processing:         PATBEG  irib  wing:nrib
    processing:             CPOINT  I  AT  xmin  -wing:ytip*irib/(wing:nrib+1)
    processing:             CPOINT  J  AT  xmax  y@I
    processing:             LINE    .   I  J  tagComp=riteWing  tagType=rib   tagIndex=!val2str(irib,0)
    processing:         PATEND
    processing:             CPOINT  I  AT  xmin  -wing:ytip*irib/(wing:nrib+1)
    processing:             CPOINT  J  AT  xmax  y@I
    processing:             LINE    .   I  J  tagComp=riteWing  tagType=rib   tagIndex=!val2str(irib,0)
    processing:         PATEND
    processing:             CPOINT  I  AT  xmin  -wing:ytip*irib/(wing:nrib+1)
    processing:             CPOINT  J  AT  xmax  y@I
    processing:             LINE    .   I  J  tagComp=riteWing  tagType=rib   tagIndex=!val2str(irib,0)
    processing:         PATEND
    processing: 
    processing:         # root rib
    processing:         CPOINT  I  AT  xmin  0
    processing:         CPOINT  J  AT  xmax  y@I
    processing:         LINE    .   I  J  tagComp=rootWing  tagType=rib   tagIndex=0
    processing: 
    processing:         # left spars
    processing:         POINT  E   AT  x@E  -y@E
    processing:         POINT  F   AT  x@F  -y@F
    processing:         LINE   FE  F   E  tagComp=leftWing  tagType=spar  tagIndex=1
    processing: 
    processing:         POINT  G   AT  x@G  -y@G
    processing:         POINT  H   AT  x@H  -y@H
    processing:         LINE   HG  H   G  tagComp=leftWing  tagType=spar tagIndex=2
    processing: 
    processing:         # left ribs
    processing:         PATBEG  irib  wing:nrib
    processing:             CPOINT  I  AT  xmin  wing:ytip*irib/(wing:nrib+1)
    processing:             CPOINT  J  AT  xmax  y@I
    processing:             LINE    .   I  J  tagComp=leftWing  tagType=rib   tagIndex=!val2str(irib,0)
    processing:         PATEND
    processing:             CPOINT  I  AT  xmin  wing:ytip*irib/(wing:nrib+1)
    processing:             CPOINT  J  AT  xmax  y@I
    processing:             LINE    .   I  J  tagComp=leftWing  tagType=rib   tagIndex=!val2str(irib,0)
    processing:         PATEND
    processing:             CPOINT  I  AT  xmin  wing:ytip*irib/(wing:nrib+1)
    processing:             CPOINT  J  AT  xmax  y@I
    processing:             LINE    .   I  J  tagComp=leftWing  tagType=rib   tagIndex=!val2str(irib,0)
    processing:         PATEND
                          Body     17 created  (toler= 1.0000e-07, nnode=  64, nedge= 106, nface=  37)
    executing [ 218] translate:      0.00000      0.00000     -0.13316
                          Body     18 created  (toler= 1.0000e-07, nnode=  64, nedge= 106, nface=  37)
    executing [ 219] store:      WingWaffle      0.00000      0.00000
                          Body     18 stored
    executing [ 221] udprim:     $/capsViews (scripted code)
              [ 222] interface:  .  ALL      0.00000
    executing [ 223] ifthen:             0.00000  NE      0.00000  and  ...
    executing [ 268] ifthen:             0.00000  NE      0.00000  and  ...
    executing [ 409] ifthen:             1.00000  NE      0.00000  and      0.00000  eq      0.00000
    executing [ 410] udprim:     $/viewCFDInviscid (scripted code)
              [ 411] interface:  .  ALL      0.00000
    executing [ 412] set:            cfdAIMs  $tetgenAIM;aflr3AIM;aflr4AIM;pointwiseAIM;su2AIM;fun3dAIM
                          cfdAIMs = $tetgenAIM;aflr3AIM;aflr4AIM;pointwiseAIM;su2AIM;fun3dAIM
    executing [ 413] set:            AFLR4_Cmp_Fuse  1
                          AFLR4_Cmp_Fuse =     1.00000     0.00000
    executing [ 414] set:            AFLR4_Cmp_Wing  2
                          AFLR4_Cmp_Wing =     2.00000     0.00000
    executing [ 415] set:            AFLR4_Cmp_Htail  3
                          AFLR4_Cmp_Htail =     3.00000     0.00000
    executing [ 416] set:            AFLR4_Cmp_Vtail  4
                          AFLR4_Cmp_Vtail =     4.00000     0.00000
    executing [ 417] set:            AFLR4_Cmp_Pod  5
                          AFLR4_Cmp_Pod =     5.00000     0.00000
    executing [ 418] set:            AFLR4_Cmp_Farfield  6
                          AFLR4_Cmp_Farfield =     6.00000     0.00000
    executing [ 419] ifthen:             1.00000  EQ      1.00000  and      0.00000  eq      0.00000
    executing [ 420] set:            MESH:SIZE  1
                          MESH:SIZE =     1.00000     0.00000
    executing [ 422] set:            ffxmin  1e3
                          ffxmin =  1000.00000     0.00000
    executing [ 423] set:            ffxmax  -1e3
                          ffxmax = -1000.00000     0.00000
    executing [ 424] set:            ffymin  1e3
                          ffymin =  1000.00000     0.00000
    executing [ 425] set:            ffymax  -1e3
                          ffymax = -1000.00000     0.00000
    executing [ 426] set:            ffzmin  1e3
                          ffzmin =  1000.00000     0.00000
    executing [ 427] set:            ffzmax  -1e3
                          ffzmax = -1000.00000     0.00000
    executing [ 428] ifthen:             0.00000  EQ      1.00000  and  ...
    executing [ 448] ifthen:             1.00000  EQ      1.00000  and      0.00000  eq      0.00000
    executing [ 449] restore:    WingOml      0.00000
                          Body     19 restored (toler= 1.0000e-07, nnode=   6, nedge=  10, nface=   6)
    executing [ 450] store:      WingOml_CFD      0.00000      1.00000
                          Body     19 stored
    executing [ 451] set:            xmax  @xmax
                          xmax =     2.37421     0.00000
    executing [ 452] set:            zmin  @zmin
                          zmin =    -0.03316     0.00000
    executing [ 453] set:            zmax  @zmax
                          zmax =     0.39990     0.00000
    executing [ 454] udprim:     $/ffbox (scripted code)
              [ 455] interface:  .  ALL      0.00000
    executing [ 456] set:            ffxmin  min(ffxmin,@xmin)
                          ffxmin =    -0.00102     0.00000
    executing [ 457] set:            ffxmax  max(ffxmax,@xmax)
                          ffxmax =     2.37421     0.00000
    executing [ 458] set:            ffymin  min(ffymin,@ymin)
                          ffymin =    -3.87298     0.00000
    executing [ 459] set:            ffymax  max(ffymax,@ymax)
                          ffymax =     3.87298     0.00000
    executing [ 460] set:            ffzmin  min(ffzmin,@zmin)
                          ffzmin =    -0.03316     0.00000
    executing [ 461] set:            ffzmax  max(ffzmax,@zmax)
                          ffzmax =     0.39990     0.00000
    executing [ 462] end:
    executing [ 463] udprim:     editAttr filename tmp_OpenCSM_00/01 (compiled code)
    processing:         FACE HAS      tagType=upper

    processing:         SET           capsBound=upperWing

    processing: 

    processing:         FACE HAS      tagType=lower

    processing:         SET           capsBound=lowerWing

    processing: 

    processing:         FACE HAS      tagType=tip tagIndex=1

    processing:         SET           capsBound=leftTip

    processing: 

    processing:         FACE HAS      tagType=tip tagIndex=2

    processing:         SET           capsBound=riteTip

                          Body     20 created  (toler= 1.0000e-07, nnode=   6, nedge=  10, nface=   6)
    executing [ 464] ifthen:             0.00000  EQ      1.00000  and  ...
    executing [ 566] select:   face
                     putting Branch Attributes on Face 1
                     putting Branch Attributes on Face 2
                     putting Branch Attributes on Face 3
                     putting Branch Attributes on Face 4
                     putting Branch Attributes on Face 5
                     putting Branch Attributes on Face 6
    executing [ 567] ifthen:             0.00000  EQ      1.00000  and  ...
    executing [ 569] else:
    executing [ 570] store:      WingOml_CFD      0.00000      0.00000
WARNING:: storage WingOml_CFD (0) is being overwritten
                          Body     20 stored
    executing [ 573] ifthen:             0.00000  EQ      1.00000  and  ...
    executing [ 697] ifthen:             0.00000  EQ      1.00000  and  ...
    executing [ 821] ifthen:             0.00000  EQ      1.00000  and  ...
    executing [ 824] ifthen:             0.00000  EQ      1.00000  and  ...
    executing [ 827] else:
    executing [ 828] ifthen:             1.00000  EQ      1.00000  and      0.00000  eq      0.00000
    executing [ 829] restore:    WingOml_CFD      0.00000
                          Body     21 restored (toler= 1.0000e-07, nnode=   6, nedge=  10, nface=   6)
    executing [ 830] select:   body
                    putting Branch Attributes on Body
    executing [ 832] ifthen:             0.00000  EQ      1.00000  and  ...
    executing [ 836] ifthen:             0.00000  EQ      1.00000  and  ...
    executing [ 841] ifthen:             0.00000  EQ      1.00000  and  ...
    executing [ 847] set:            size  20*max(ffxmax-ffxmin,ffymax-ffymin)
                          size =   154.91934     0.00000
    executing [ 848] box:          -76.27307    -77.45967    -77.27630    154.91934    154.91934    154.91934
                          Body     22 created  (toler= 1.0000e-07, nnode=   8, nedge=  12, nface=   6)
    executing [ 849] select:   body
                    putting Branch Attributes on Body
    executing [ 850] end:
    executing [ 852] ifthen:             0.00000  NE      0.00000  and  ...
    executing [1290] ifthen:             1.00000  NE      0.00000  OR  ...
    executing [1291] udprim:     $/viewStructure (scripted code)
              [1292] interface:  .  ALL      0.00000
    executing [1293] set:            structAIMs  $nastranAIM;astrosAIM;mystranAIM;egadsTessAIM
                          structAIMs = $nastranAIM;astrosAIM;mystranAIM;egadsTessAIM
    executing [1294] ifthen:             1.00000  EQ      1.00000  and      0.00000  eq      0.00000
    executing [1295] restore:    WingOml      0.00000
                          Body     23 restored (toler= 1.0000e-07, nnode=   6, nedge=  10, nface=   6)
    executing [1296] restore:    WingWaffle      0.00000
                          Body     24 restored (toler= 1.0000e-07, nnode=  64, nedge= 106, nface=  37)
    executing [1297] intersect:  none      1.00000   0.0000e+00
                          Body     25 created  (toler= 5.0000e-06, nnode=  50, nedge=  92, nface=  37)
    executing [1298] restore:    WingOml      0.00000
                          Body     26 restored (toler= 1.0000e-07, nnode=   6, nedge=  10, nface=   6)
    executing [1299] restore:    WingWaffle      0.00000
                          Body     27 restored (toler= 1.0000e-07, nnode=  64, nedge= 106, nface=  37)
    executing [1300] subtract:   none      1.00000   0.0000e+00
                          Body     28 created  (toler= 1.0749e-06, nnode=  54, nedge= 106, nface=  54)
    executing [1301] extract:    0
                          Body     29 created  (toler= 1.0749e-06, nnode=  54, nedge= 106, nface=  54)
    executing [1302] union:          0.00000  0   0.0000e+00
                          Body     30 created  (toler= 5.0000e-06, nnode=  54, nedge= 120, nface=  91)
    executing [1303] ifthen:             0.00000  EQ      1.00000  and  ...
    executing [1306] else:
    executing [1307] udprim:     editAttr filename tmp_OpenCSM_00/05 (compiled code)
    processing:             FACE HAS        tagComp=leftWing

    processing:             SET             capsGroup=leftWingSkin

    processing:     

    processing:             FACE HAS        tagComp=riteWing

    processing:             SET             capsGroup=riteWingSkin

    processing:     

    processing:             FACE HAS        tagType=tip

    processing:             SET             capsGroup=wingRib

    processing:     

    processing:             FACE HAS        tagType=trailingEdge

    processing:             SET             capsGroup=wingTE

    processing:     

    processing:             FACE HAS        tagType=rib

    processing:             SET             capsGroup=wingRib

    processing: 

    processing:             FACE HAS        tagType=spar tagIndex=1

    processing:             SET             capsGroup=wingSpar1

    processing:             SET             capsMesh=wingSpar1

    processing: 

    processing:             FACE HAS        tagType=spar tagIndex=2

    processing:             SET             capsGroup=wingSpar2

    processing:             SET             capsMesh=wingSpar2

WARNING:: toler =   5.0000e-06 for UDPRIM
                          Body     31 created  (toler= 5.0000e-06, nnode=  54, nedge= 120, nface=  91)
    executing [1309] udprim:     editAttr filename tmp_OpenCSM_00/06 (compiled code)
    processing:         FACE HAS      tagType=upper

    processing:         SET           capsBound=upperWing

    processing: 

    processing:         FACE HAS      tagType=lower

    processing:         SET           capsBound=lowerWing

    processing: 

    processing:         FACE HAS      tagType=tip tagIndex=1

    processing:         SET           capsBound=leftTip

    processing: 

    processing:         FACE HAS      tagType=tip tagIndex=2

    processing:         SET           capsBound=riteTip

WARNING:: toler =   5.0000e-06 for UDPRIM
                          Body     32 created  (toler= 5.0000e-06, nnode=  54, nedge= 120, nface=  91)
    executing [1310] udprim:     editAttr filename tmp_OpenCSM_00/07 (compiled code)
    processing:         NODE ADJ2FACE tagComp=leftWing tagType=tip

    processing:         AND  ADJ2FACE tagType=lower

    processing:         AND  ADJ2FACE tagType=spar tagIndex=1

    processing:         SET           capsLoad=leftPointLoad

    processing: 

    processing:         NODE ADJ2FACE tagComp=riteWing tagType=tip

    processing:         AND  ADJ2FACE tagType=lower

    processing:         AND  ADJ2FACE tagType=spar tagIndex=1

    processing:         SET           capsLoad=ritePointLoad

WARNING:: toler =   5.0000e-06 for UDPRIM
                          Body     33 created  (toler= 5.0000e-06, nnode=  54, nedge= 120, nface=  91)
    executing [1311] select:   edge  tagType  leadingEdge  *  *  *  *
    executing [1312] dimension:     leadingEdges      1.00000      8.00000
    executing [1313] set:            leadingEdges  @sellist
                          leadingEdges[1,1] =     8.00000     0.00000
                          leadingEdges[1,2] =    31.00000     0.00000
                          leadingEdges[1,3] =    33.00000     0.00000
                          leadingEdges[1,4] =    59.00000     0.00000
                          leadingEdges[1,5] =    61.00000     0.00000
                          leadingEdges[1,6] =    87.00000     0.00000
                          leadingEdges[1,7] =    89.00000     0.00000
                          leadingEdges[1,8] =   110.00000     0.00000
    executing [1314] patbeg:         i      8.00000
                          pattern counter: i =   1
    executing [1315] select:   edge  8
                     putting Branch Attributes on Edge 8
    executing [1316] patend:
                          pattern counter: i =   2
    executing [1315] select:   edge  31
                     putting Branch Attributes on Edge 31
    executing [1316] patend:
                          pattern counter: i =   3
    executing [1315] select:   edge  33
                     putting Branch Attributes on Edge 33
    executing [1316] patend:
                          pattern counter: i =   4
    executing [1315] select:   edge  59
                     putting Branch Attributes on Edge 59
    executing [1316] patend:
                          pattern counter: i =   5
    executing [1315] select:   edge  61
                     putting Branch Attributes on Edge 61
    executing [1316] patend:
                          pattern counter: i =   6
    executing [1315] select:   edge  87
                     putting Branch Attributes on Edge 87
    executing [1316] patend:
                          pattern counter: i =   7
    executing [1315] select:   edge  89
                     putting Branch Attributes on Edge 89
    executing [1316] patend:
                          pattern counter: i =   8
    executing [1315] select:   edge  110
                     putting Branch Attributes on Edge 110
    executing [1316] patend:
    executing [1317] udprim:     editAttr filename tmp_OpenCSM_00/08 (compiled code)
    processing:         FACE ADJ2EDGE tagComp=leftWing

    processing:         SET           tagTemp=leadingEdgeFace

WARNING:: toler =   5.0000e-06 for UDPRIM
                          Body     34 created  (toler= 5.0000e-06, nnode=  54, nedge= 120, nface=  91)
    executing [1318] udprim:     editAttr filename tmp_OpenCSM_00/09 (compiled code)
    processing:         EDGE ADJ2FACE tagTemp=leadingEdgeFace

    processing:         AND  ADJ2FACE tagComp=rootWing

    processing:         SET           capsMesh=rootLeadingEdge

WARNING:: toler =   5.0000e-06 for UDPRIM
                          Body     35 created  (toler= 5.0000e-06, nnode=  54, nedge= 120, nface=  91)
    executing [1319] ifthen:             1.00000  EQ      1.00000  and      0.00000  eq      0.00000
    executing [1320] udprim:     editAttr filename tmp_OpenCSM_00/10 (compiled code)
    processing:             FACE HAS      tagComp=rootWing

    processing:             SET           capsConstraint=rootConstraint

    processing:        

    processing:             EDGE ADJ2FACE tagComp=rootWing

    processing:             SET  capsConstraint=rootConstraint

    processing:     

    processing:             NODE ADJ2FACE tagComp=rootWing

    processing:             SET  capsConstraint=rootConstraint

WARNING:: toler =   5.0000e-06 for UDPRIM
                          Body     36 created  (toler= 5.0000e-06, nnode=  54, nedge= 120, nface=  91)
    executing [1322] ifthen:             0.00000  EQ      1.00000  and  ...
    executing [1325] udprim:     editAttr filename tmp_OpenCSM_00/12 (compiled code)
    processing:         FACE HAS      tagComp=leftWing tagType=upper

    processing:         AND  ADJ2EDGE tagType=leadingEdge

    processing:         AND  ADJ2FACE tagComp=riteWing

    processing:         SET           tagCsys=leftWing

    processing: 

    processing:         FACE HAS      tagComp=riteWing tagType=upper

    processing:         AND  ADJ2EDGE tagType=leadingEdge

    processing:         AND  ADJ2FACE tagComp=leftWing

    processing:         SET           tagCsys=riteWing

WARNING:: toler =   5.0000e-06 for UDPRIM
                          Body     37 created  (toler= 5.0000e-06, nnode=  54, nedge= 120, nface=  91)
    executing [1326] select:   face  tagCsys  leftWing  *  *  *  *
    executing [1327] set:            leftWingSkinCsys  @sellist
                          leftWingSkinCsys =    27.00000     0.00000
    executing [1328] select:   face  tagCsys  riteWing  *  *  *  *
    executing [1329] set:            riteWingSkinCsys  @sellist
                          riteWingSkinCsys =     8.00000     0.00000
    executing [1330] store:      WingStruct      0.00000      0.00000
                          Body     37 stored
    executing [1331] restore:    WingStruct      0.00000
                          Body     38 restored (toler= 5.0000e-06, nnode=  54, nedge= 120, nface=  91)
    executing [1332] store:      WingStruct      0.00000      0.00000
WARNING:: storage WingStruct (0) is being overwritten
                          Body     38 stored
    executing [1334] restore:    WingStruct      0.00000
                          Body     39 restored (toler= 5.0000e-06, nnode=  54, nedge= 120, nface=  91)
    executing [1335] select:   body
                    putting Branch Attributes on Body
    executing [1336] ifthen:             0.00000  EQ      1.00000  and  ...
    executing [1339] end:
    executing [1341] ifthen:             0.00000  NE      0.00000  and  ...
    executing [1378] end:
    finalizing:
==> Profile information
    Branch type           ncall  time (sec)    pct
    dimension                 1       0.000    0.0
    box                       1       0.001    0.0
    udprim                   16       0.469    1.2
    restore                  10       0.046    0.1
    rule                      1       0.085    0.2
    intersect                 1       3.847   10.1
    subtract                  1       4.648   12.2
    union                     1      27.930   73.3
    join                      1       0.133    0.3
    extract                   1       0.766    2.0
    translate                 2       0.023    0.1
    rotatex                   2       0.003    0.0
    rotatey                   1       0.001    0.0
    scale                     2       0.003    0.0
    mirror                    1       0.033    0.1
    interface                 5       0.000    0.0
    end                       5       0.000    0.0
    set                      93       0.001    0.0
    udparg                    3       0.000    0.0
    select                   28       0.124    0.3
    store                     8       0.000    0.0
    patbeg                    1       0.000    0.0
    patend                    8       0.000    0.0
    ifthen                   57       0.001    0.0
    else                      4       0.000    0.0
    endif                    57       0.000    0.0
    catbeg                    1       0.000    0.0
    mark                      1       0.000    0.0
    Total                   313      38.115
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 2
	Name = Wing, index = 1
	Name = Farfield, index = 2
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 2
	Name = Wing, index = 1
	Name = Farfield, index = 2

Getting mesh sizing parameters
	Mesh sizing name - Wing
	Mesh sizing name - Farfield
	Done getting mesh sizing parameters
 
AFLR2    : ---------------------------------------
AFLR2    : AFLR2 LIBRARY
AFLR2    : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR2    : TRIA/QUAD GRID GENERATOR
AFLR2    : Version Number 9.13.13
AFLR2    : Version Date   10/10/20 @ 10:50PM
AFLR2    : Compile OS     Darwin 19.6.0 x86_64
AFLR2    : Compile Date   10/10/20 @ 10:50PM
AFLR2    : Copyright 1994-2020, D.L. Marcum
AFLR2    : ---------------------------------------
 
AFLR4    : ---------------------------------------
AFLR4    : AFLR4 LIBRARY
AFLR4    : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR4    : TRIA/QUAD SURFACE GRID GENERATOR
AFLR4    : Version Number 10.11.10
AFLR4    : Version Date   10/30/20 @ 03:19PM
AFLR4    : Compile OS     Darwin 19.6.0 x86_64
AFLR4    : Compile Date   10/30/20 @ 03:19PM
AFLR4    : Copyright 1994-2020, D.L. Marcum
AFLR4    : ---------------------------------------

EGADS    : EGADS CAD Geometry Setup

EGADS    : Using EGADS Version 1.19
EGADS    : Using OpenCASCADE Version ase with OpenCASCADE 7.4.1

EGADS    : Model has 2 Bodies

EGADS    : Body 0 is a SolidBody
EGADS    : Body 0 has 1 BRep Shells
EGADS    : Body 0 has 6 BRep Faces
EGADS    : Body 0 has 10 BRep Edges
EGADS    : Body 0 has 6 BRep Nodes
EGADS    : Body 1 is a SolidBody
EGADS    : Body 1 has 1 BRep Shells
EGADS    : Body 1 has 6 BRep Faces
EGADS    : Body 1 has 12 BRep Edges
EGADS    : Body 1 has 8 BRep Nodes

AFLR4    : Surface Mesh Spacing Setup

AFLR4    : Max Bounding Box Length     = 154.919
AFLR4    : Min Bounding Box Length     = 154.919
AFLR4    : Max Ref Bounding Box Length = 7.74597
AFLR4    : Min Ref Bounding Box Length = 0.433058
AFLR4    : Reference Length            = 6.45497
AFLR4    : BL Thickness                = 0
AFLR4    : FarField Spacing            = 21.0478
AFLR4    : Abs Min Surf Spacing        = 0.0161374
AFLR4    : Min Surf Spacing            = 0.0322749
AFLR4    : Max Surf Spacing            = 0.645497

AFLR4    : Check Grid BCs

AFLR4    : Grid BCs are OK

AFLR4    : Geometry Definition Information

AFLR4    : IER = Isolated Edge Refinement
AFLR4    : ER  = Edge Refinement

AFLR4    : Definition         Definition  Composite             Grid BC       IER        ER     Scale
AFLR4    :         ID               Type         ID                Type      Flag    Weight    Factor
AFLR4    :          0 glue-only composite         -                   -         -         -         -
AFLR4    :          1        CAD geometry         0            STD w/BL         1         1         1
AFLR4    :          2        CAD geometry         0            STD w/BL         1         1         1
AFLR4    :          3        CAD geometry         0            STD w/BL         1         1         1
AFLR4    :          4        CAD geometry         0            STD w/BL         1         1         1
AFLR4    :          5        CAD geometry         0            STD w/BL         1         1         1
AFLR4    :          6        CAD geometry         0            STD w/BL         1         1         1
AFLR4    :          7        CAD geometry         0            FARFIELD         1         0         1
AFLR4    :          8        CAD geometry         0            FARFIELD         1         0         1
AFLR4    :          9        CAD geometry         0            FARFIELD         1         0         1
AFLR4    :         10        CAD geometry         0            FARFIELD         1         0         1
AFLR4    :         11        CAD geometry         0            FARFIELD         1         0         1
AFLR4    :         12        CAD geometry         0            FARFIELD         1         0         1

AFLR4    : Definition Neighbor Map

AFLR4    : Definition   Neighbor-Definitions
AFLR4    :          1   4 2 3
AFLR4    :          2   1 5 3
AFLR4    :          3   1 2
AFLR4    :          4   1 5 6
AFLR4    :          5   2 4 6
AFLR4    :          6   4 5
AFLR4    :          7   9 12 10 11
AFLR4    :          8   9 12 10 11
AFLR4    :          9   7 8 11 12
AFLR4    :         10   7 8 11 12
AFLR4    :         11   7 8 9 10
AFLR4    :         12   7 8 9 10

AFLR4    : Define CAD surface definition 1
AFLR4    : Define CAD surface definition 2
AFLR4    : Define CAD surface definition 3
AFLR4    : Define CAD surface definition 4
AFLR4    : Define CAD surface definition 5
AFLR4    : Define CAD surface definition 6
AFLR4    : Define CAD surface definition 7
AFLR4    : Define CAD surface definition 8
AFLR4    : Define CAD surface definition 9
AFLR4    : Define CAD surface definition 10
AFLR4    : Define CAD surface definition 11
AFLR4    : Define CAD surface definition 12

AFLR4    : Surface Grid Generation

AFLR4    : Generate optimal mesh on surface definition 1
AFLR2    : Nodes, Faces      =      1364      2547
AFLR4    : Nodes, Faces      =      1007      1833

AFLR4    : Generate optimal mesh on surface definition 2
AFLR2    : Nodes, Faces      =      1335      2491
AFLR4    : Nodes, Faces      =       952      1725

AFLR4    : Generate optimal mesh on surface definition 3
AFLR2    : Nodes, Faces      =        48        65
AFLR4    : Nodes, Faces      =        44        57

AFLR4    : Generate optimal mesh on surface definition 4
AFLR2    : Nodes, Faces      =      1368      2555
AFLR4    : Nodes, Faces      =      1005      1829

AFLR4    : Generate optimal mesh on surface definition 5
AFLR2    : Nodes, Faces      =      1330      2481
AFLR4    : Nodes, Faces      =       944      1709

AFLR4    : Generate optimal mesh on surface definition 6
AFLR2    : Nodes, Faces      =        48        65
AFLR4    : Nodes, Faces      =        44        57

AFLR4    : Generate optimal mesh on surface definition 7
AFLR2    : Nodes, Faces      =        73       116
AFLR4    : Nodes, Faces      =        68       106

AFLR4    : Generate optimal mesh on surface definition 8
AFLR2    : Nodes, Faces      =        73       116
AFLR4    : Nodes, Faces      =        68       106

AFLR4    : Generate optimal mesh on surface definition 9
AFLR2    : Nodes, Faces      =        73       116
AFLR4    : Nodes, Faces      =        68       106

AFLR4    : Generate optimal mesh on surface definition 10
AFLR2    : Nodes, Faces      =        73       116
AFLR4    : Nodes, Faces      =        68       106

AFLR4    : Generate optimal mesh on surface definition 11
AFLR2    : Nodes, Faces      =        73       116
AFLR4    : Nodes, Faces      =        68       106

AFLR4    : Generate optimal mesh on surface definition 12
AFLR2    : Nodes, Faces      =        73       116
AFLR4    : Nodes, Faces      =        68       106

DGEOM    : Add surface definitions to composite definition 0
DGEOM    : Glue composite surface definition 0
DGEOM    : Nodes, Faces      =      3927      7846

AFLR4    : Curvature BG Surface Grid Generation

AFLR4    : Nodes, Faces      =      3927      7846

AFLR4    : Surface Grid Generation

AFLR4    : Generate optimal mesh on surface definition 1
AFLR2    : Nodes, Faces      =      3393      6475
AFLR4    : Nodes, Faces      =      2440      4569

AFLR4    : Generate optimal mesh on surface definition 2
AFLR2    : Nodes, Faces      =      3382      6454
AFLR4    : Nodes, Faces      =      2273      4236

AFLR4    : Generate optimal mesh on surface definition 3
AFLR2    : Nodes, Faces      =       145       226
AFLR4    : Nodes, Faces      =       137       210

AFLR4    : Generate optimal mesh on surface definition 4
AFLR2    : Nodes, Faces      =      3394      6477
AFLR4    : Nodes, Faces      =      2423      4535

AFLR4    : Generate optimal mesh on surface definition 5
AFLR2    : Nodes, Faces      =      3402      6494
AFLR4    : Nodes, Faces      =      2288      4266

AFLR4    : Generate optimal mesh on surface definition 6
AFLR2    : Nodes, Faces      =       145       226
AFLR4    : Nodes, Faces      =       137       210

AFLR4    : Generate optimal mesh on surface definition 7
AFLR2    : Nodes, Faces      =        73       116
AFLR4    : Nodes, Faces      =        68       106

AFLR4    : Generate optimal mesh on surface definition 8
AFLR2    : Nodes, Faces      =        73       116
AFLR4    : Nodes, Faces      =        68       106

AFLR4    : Generate optimal mesh on surface definition 9
AFLR2    : Nodes, Faces      =        73       116
AFLR4    : Nodes, Faces      =        68       106

AFLR4    : Generate optimal mesh on surface definition 10
AFLR2    : Nodes, Faces      =        73       116
AFLR4    : Nodes, Faces      =        68       106

AFLR4    : Generate optimal mesh on surface definition 11
AFLR2    : Nodes, Faces      =        73       116
AFLR4    : Nodes, Faces      =        68       106

AFLR4    : Generate optimal mesh on surface definition 12
AFLR2    : Nodes, Faces      =        73       116
AFLR4    : Nodes, Faces      =        68       106

DGEOM    : Add surface definitions to composite definition 0
DGEOM    : Glue composite surface definition 0
DGEOM    : Nodes, Faces      =      9335     18662

OVERALL  : CPU Time          =     0.279   seconds

AFLR4    : GET EGADS TESS FROM AFLR4 DATA

AFLR4    : EGADS TESS CREATED WITHOUT ERROR

AFLR4    : CHECK COORDINATES OF EGADS TESSELLATION

AFLR4    : CAD Definition=         1 Max Coordinate Deviation=0.000000e+00
AFLR4    : CAD Definition=         2 Max Coordinate Deviation=0.000000e+00
AFLR4    : CAD Definition=         3 Max Coordinate Deviation=0.000000e+00
AFLR4    : CAD Definition=         4 Max Coordinate Deviation=0.000000e+00
AFLR4    : CAD Definition=         5 Max Coordinate Deviation=0.000000e+00
AFLR4    : CAD Definition=         6 Max Coordinate Deviation=0.000000e+00
AFLR4    : CAD Definition=         1 Max Coordinate Deviation=0.000000e+00
AFLR4    : CAD Definition=         2 Max Coordinate Deviation=0.000000e+00
AFLR4    : CAD Definition=         3 Max Coordinate Deviation=0.000000e+00
AFLR4    : CAD Definition=         4 Max Coordinate Deviation=0.000000e+00
AFLR4    : CAD Definition=         5 Max Coordinate Deviation=0.000000e+00
AFLR4    : CAD Definition=         6 Max Coordinate Deviation=0.000000e+00

AFLR4    : COORDINATES OF EGADS TESSELLATION CHECKED WITHOUT ERROR

AFLR4    : CHECK AFLR4 AND EGADS TRIA-FACE ORDERING

AFLR4    : CAD Definition=         1 Ordering OK
AFLR4    : CAD Definition=         2 Ordering OK
AFLR4    : CAD Definition=         3 Ordering OK Reversed
AFLR4    : CAD Definition=         4 Ordering OK Reversed
AFLR4    : CAD Definition=         5 Ordering OK Reversed
AFLR4    : CAD Definition=         6 Ordering OK
AFLR4    : CAD Definition=         7 Ordering OK Reversed
AFLR4    : CAD Definition=         8 Ordering OK
AFLR4    : CAD Definition=         9 Ordering OK Reversed
AFLR4    : CAD Definition=        10 Ordering OK
AFLR4    : CAD Definition=        11 Ordering OK Reversed
AFLR4    : CAD Definition=        12 Ordering OK

AFLR4    : AFLR4 AND EGADS TRIA-FACE ORDERING CHECKED WITHOUT ERROR

Body = 1
Number of nodes = 9015
Number of elements = 18026
Number of tris = 18026
Number of quad = 0
Body = 2
Number of nodes = 320
Number of elements = 636
Number of tris = 636
Number of quad = 0
----------------------------
Total number of nodes = 9335
Total number of elements = 18662
Found link for groupMap (Attribute_Map) from parent
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 2
	Name = Wing, index = 1
	Name = Farfield, index = 2
Found link for a surface mesh (Surface_Mesh) from parent
Number of surface nodes - 9335
Number of surface elements - 18662
Getting volume mesh
 
UG PARAM : SETTING INPUT PARAMETERS FROM ARGUMENT VECTOR
 
UG PARAM : mrecm                       = 3         
UG PARAM : mrecqm                      = 3         
 
AFLR3    : ---------------------------------------
AFLR3    : AFLR3 LIBRARY
AFLR3    : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR3    : TETRAHEDRAL GRID GENERATOR
AFLR3    : Version Number 16.30.16
AFLR3    : Version Date   10/10/20 @ 03:34PM
AFLR3    : Compile OS     Darwin 19.6.0 x86_64
AFLR3    : Compile Date   10/11/20 @ 12:50AM
AFLR3    : Copyright 1994-2020, D.L. Marcum
AFLR3    : ---------------------------------------
 
AFLR3 IC : INPUT SURFACE GRID CHECK
 
AFLR3 IC : Nodes, Elements   =      9335         0
 
AFLR3    : CPU Time          =     0.020   seconds
 
AFLR3 IG : INITIAL VOLUME GRID GENERATION
 
AFLR3 IG : Nodes, Elements   =      9335         0
AFLR3 IG : Nodes, Elements   =         8        10
AFLR3 IG : Nodes, Elements   =      1868     12802
AFLR3 IG : Nodes, Elements   =      3736     26174
AFLR3 IG : Nodes, Elements   =      5604     39996
AFLR3 IG : Nodes, Elements   =      7472     54696
AFLR3 IG : Nodes, Elements   =      9340     70160
AFLR3 IG : Nodes, Elements   =      9342     70214
AFLR3 IG : Nodes, Elements   =      9342     70038
AFLR3 IG : Nodes, Elements   =      9342     65457
AFLR3 IG : Nodes, Elements   =      9342     63853
AFLR3 IG : Nodes, Elements   =      9335     36678
AFLR3 IG : Nodes, Elements   =      9335     42586
AFLR3 IG : Nodes, Elements   =      9335     30432
AFLR3 IG : Nodes, Elements   =      9335     28327
 
AFLR3    : CPU Time          =     0.300   seconds
 
AFLR3 GG : ISOTROPIC VOLUME GRID GENERATION
 
AFLR3 GG : Nodes, Elements   =      9335     28327
AFLR3 GG : Nodes, Elements   =     13664     41383
AFLR3 GG : Nodes, Elements   =     13664     58327
AFLR3 GG : Nodes, Elements   =     13664     53926
AFLR3 GG : Nodes, Elements   =     17251     65070
AFLR3 GG : Nodes, Elements   =     17251     79156
AFLR3 GG : Nodes, Elements   =     17251     74584
AFLR3 GG : Nodes, Elements   =     20911     85936
AFLR3 GG : Nodes, Elements   =     20911    100204
AFLR3 GG : Nodes, Elements   =     20911     96106
AFLR3 GG : Nodes, Elements   =     24578    107285
AFLR3 GG : Nodes, Elements   =     24578    122135
AFLR3 GG : Nodes, Elements   =     24578    118000
AFLR3 GG : Nodes, Elements   =     28268    129223
AFLR3 GG : Nodes, Elements   =     28268    143781
AFLR3 GG : Nodes, Elements   =     28268    139869
AFLR3 GG : Nodes, Elements   =     31926    150933
AFLR3 GG : Nodes, Elements   =     31926    165332
AFLR3 GG : Nodes, Elements   =     31926    161553
AFLR3 GG : Nodes, Elements   =     35485    172289
AFLR3 GG : Nodes, Elements   =     35485    186302
AFLR3 GG : Nodes, Elements   =     35485    182688
AFLR3 GG : Nodes, Elements   =     39014    193325
AFLR3 GG : Nodes, Elements   =     39014    207191
AFLR3 GG : Nodes, Elements   =     39014    203616
AFLR3 GG : Nodes, Elements   =     42380    213746
AFLR3 GG : Nodes, Elements   =     42380    226774
AFLR3 GG : Nodes, Elements   =     42380    223470
AFLR3 GG : Nodes, Elements   =     45594    233143
AFLR3 GG : Nodes, Elements   =     45594    245701
AFLR3 GG : Nodes, Elements   =     45594    242579
AFLR3 GG : Nodes, Elements   =     48680    251862
AFLR3 GG : Nodes, Elements   =     48680    263885
AFLR3 GG : Nodes, Elements   =     48680    260843
AFLR3 GG : Nodes, Elements   =     51607    269642
AFLR3 GG : Nodes, Elements   =     51607    281129
AFLR3 GG : Nodes, Elements   =     51607    278242
AFLR3 GG : Nodes, Elements   =     54466    286829
AFLR3 GG : Nodes, Elements   =     54466    298009
AFLR3 GG : Nodes, Elements   =     54466    295289
AFLR3 GG : Nodes, Elements   =     57175    303426
AFLR3 GG : Nodes, Elements   =     57175    314032
AFLR3 GG : Nodes, Elements   =     57175    311347
AFLR3 GG : Nodes, Elements   =     59734    319030
AFLR3 GG : Nodes, Elements   =     59734    329059
AFLR3 GG : Nodes, Elements   =     59734    326537
AFLR3 GG : Nodes, Elements   =     62197    333935
AFLR3 GG : Nodes, Elements   =     62197    343560
AFLR3 GG : Nodes, Elements   =     62197    341234
AFLR3 GG : Nodes, Elements   =     64493    348127
AFLR3 GG : Nodes, Elements   =     64493    357104
AFLR3 GG : Nodes, Elements   =     64493    354919
AFLR3 GG : Nodes, Elements   =     66655    361408
AFLR3 GG : Nodes, Elements   =     66655    369771
AFLR3 GG : Nodes, Elements   =     66655    367737
AFLR3 GG : Nodes, Elements   =     68691    373851
AFLR3 GG : Nodes, Elements   =     68691    381683
AFLR3 GG : Nodes, Elements   =     68691    379827
AFLR3 GG : Nodes, Elements   =     70623    385623
AFLR3 GG : Nodes, Elements   =     70623    393122
AFLR3 GG : Nodes, Elements   =     70623    391269
AFLR3 GG : Nodes, Elements   =     72365    396500
AFLR3 GG : Nodes, Elements   =     72365    403287
AFLR3 GG : Nodes, Elements   =     72365    401668
AFLR3 GG : Nodes, Elements   =     74030    406665
AFLR3 GG : Nodes, Elements   =     74030    413119
AFLR3 GG : Nodes, Elements   =     74030    411573
AFLR3 GG : Nodes, Elements   =     75529    416071
AFLR3 GG : Nodes, Elements   =     75529    421907
AFLR3 GG : Nodes, Elements   =     75529    420507
AFLR3 GG : Nodes, Elements   =     76869    424529
AFLR3 GG : Nodes, Elements   =     76869    429740
AFLR3 GG : Nodes, Elements   =     76869    428485
AFLR3 GG : Nodes, Elements   =     78055    432045
AFLR3 GG : Nodes, Elements   =     78055    436697
AFLR3 GG : Nodes, Elements   =     78055    435531
AFLR3 GG : Nodes, Elements   =     79029    438454
AFLR3 GG : Nodes, Elements   =     79029    442292
AFLR3 GG : Nodes, Elements   =     79029    441330
AFLR3 GG : Nodes, Elements   =     79832    443739
AFLR3 GG : Nodes, Elements   =     79832    446926
AFLR3 GG : Nodes, Elements   =     79832    446120
AFLR3 GG : Nodes, Elements   =     80482    448071
AFLR3 GG : Nodes, Elements   =     80482    450702
AFLR3 GG : Nodes, Elements   =     80482    449971
AFLR3 GG : Nodes, Elements   =     80956    451393
AFLR3 GG : Nodes, Elements   =     80956    453377
AFLR3 GG : Nodes, Elements   =     80956    452794
AFLR3 GG : Nodes, Elements   =     81261    453709
AFLR3 GG : Nodes, Elements   =     81261    454931
AFLR3 GG : Nodes, Elements   =     81261    454583
AFLR3 GG : Nodes, Elements   =     81421    455063
AFLR3 GG : Nodes, Elements   =     81421    455738
AFLR3 GG : Nodes, Elements   =     81421    455501
AFLR3 GG : Nodes, Elements   =     81492    455714
AFLR3 GG : Nodes, Elements   =     81492    456042
AFLR3 GG : Nodes, Elements   =     81492    455920
AFLR3 GG : Nodes, Elements   =     81521    456007
AFLR3 GG : Nodes, Elements   =     81521    456151
AFLR3 GG : Nodes, Elements   =     81521    456083
AFLR3 GG : Nodes, Elements   =     81534    456122
AFLR3 GG : Nodes, Elements   =     81534    456170
AFLR3 GG : Nodes, Elements   =     81534    456152
AFLR3 GG : Nodes, Elements   =     81539    456167
AFLR3 GG : Nodes, Elements   =     81539    456190
AFLR3 GG : Nodes, Elements   =     81539    456179
AFLR3 GG : Nodes, Elements   =     81543    456191
AFLR3 GG : Nodes, Elements   =     81543    456211
AFLR3 GG : Nodes, Elements   =     81543    456201
 
AFLR3    : CPU Time          =     4.795   seconds
 
AFLR3 QI : QUALITY IMPROVEMENT
 
AFLR3 QI : Nodes, Elements   =     81543    456201
AFLR3 QI : Nodes, Elements   =     81135    453919
AFLR3 QI : Nodes, Elements   =     81090    453671
AFLR3 QI : Nodes, Elements   =     81087    453656
AFLR3 QI : Nodes, Elements   =     81087    455570
AFLR3 QI : Nodes, Elements   =     81087    453362
AFLR3 QI : Nodes, Elements   =     81087    452458
AFLR3 QI : Nodes, Elements   =     81087    452731
AFLR3 QI : Nodes, Elements   =     81087    452270
AFLR3 QI : Nodes, Elements   =     81087    452172
AFLR3 QI : Nodes, Elements   =     81087    452375
AFLR3 QI : Nodes, Elements   =     81087    452167
AFLR3 QI : Nodes, Elements   =     81087    452128
 
AFLR3    : CPU Time          =     1.077   seconds
 
AFLR3    : DONE

UG3      : DIHEDRAL ANGLE CHECK

UG3      : No. Tet Elems     =    452128
UG3      : Min, Max Ang      =     12.75     157.7
UG3      : Average Angle     =      70.2
UG3      : No. Angle>160.0   =         0
UG3      : No. Angle>179.9   =         0

UG3      : VOL CHECK

UG3      : Total-Volume      =  3.72e+06

UG3      : No. Tet Elems     =    452128
UG3      : Min Vol           =   1.3e-06
UG3      : Average Vol       =      8.22
UG3      : Total-Tet-Vol     =  3.72e+06
UG3      : No. Vol<TOL       =         0

UG3      : Q VOL-LENGTH-RATIO CHECK
                      2/3        2
UG3      : Q = c * Vol   / sum( L  )
UG3      : 0 <= Q <= 1

UG3      : No. Tet Elems     =    452128
UG3      : Min, Max Q        =     0.215         1
UG3      : Average Q         =       0.9
UG3      : No. Q<       0.1  =         0
UG3      : No. Q<      0.01  =         0
Volume mesh:
	Number of nodes = 81087
	Number of elements = 470790
	Number of triangles = 18662
	Number of quadrilatarals = 0
	Number of tetrahedrals = 452128
	Number of pyramids= 0
	Number of prisms= 0
	Number of hexahedrals= 0
No project name ("Proj_Name") provided - A volume mesh will not be written out
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 5
	Name = wingSpar1, index = 1
	Name = riteWingSkin, index = 2
	Name = wingRib, index = 3
	Name = leftWingSkin, index = 4
	Name = wingSpar2, index = 5
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar1, index = 1
	Name = wingSpar2, index = 2
	Name = leadingEdge, index = 3
	Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
	Tessellating body
Number of nodes = 265
Number of elements = 346
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 0
Number of quadrilateral elements = 346
----------------------------
Total number of nodes = 265
Total number of elements = 346
 su2AIM/aimDiscr: Found link for attrMap (Attribute_Map) from parent
Mapping Csys attributes ................
	Number of unique Csys attributes = 2
	Name = leftWingSkin, index = 1
	Name = riteWingSkin, index = 2

Getting FEA coordinate systems.......
	Number of coordinate systems - 2
	Coordinate system name - leftWingSkin
	Coordinate system name - riteWingSkin
Mapping capsConstraint attributes ................
	Number of unique capsConstraint attributes = 1
	Name = rootConstraint, index = 1
Mapping capsLoad attributes ................
	Number of unique capsLoad attributes = 2
	Name = ritePointLoad, index = 1
	Name = leftPointLoad, index = 2
Mapping capsBound attributes ................
	Number of unique capsBound attributes = 4
	Name = lowerWing, index = 1
	Name = upperWing, index = 2
	Name = riteTip, index = 3
	Name = leftTip, index = 4
Mapping capsConnect attributes ................
	Number of unique capsConnect attributes = 0
Mapping capsResponse attributes ................
	Number of unique capsResponse attributes = 0
Found link for attrMap (Attribute_Map) from parent
Found link for a Surface mesh from parent
Setting FEA Data
	Mesh for body = 0
	Number of nodal coordinates = 265
	Number of elements = 346
	Elemental Nodes = 0
	Elemental Rods  = 0
	Elemental Tria3 = 0
	Elemental Quad4 = 346
 CAPS Info: Reparameterization Bound -> upperWing -- nu, nv = 129 129
 CAPS Info: Reparameterization Bound -> lowerWing -- nu, nv = 129 129


Executing dataTransfer "Displacement"......

==> Running SU2 pre-analysis...
Found link for attrMap (Attribute_Map) from parent
Getting CFD boundary conditions
	Boundary condition name - Wing
	Boundary condition name - Farfield
	Done getting CFD boundary conditions
Found link for volume mesh (Volume_Mesh) from parent
Writing boundary flags
 - bcProps.surfaceProp[0].surfaceType = 1
 - bcProps.surfaceProp[1].surfaceType = 3
Done boundary flags

Writing SU2 file ....
	Binary output is not supported by SU2
	..... switching to ASCII!
Finished writing SU2 file

Writing SU2 data transfer files
Writing SU2 Motion File - aeroelasticIterative_motion.dat
Warning: The su2 cfg file will be overwritten!
Write SU2 configuration file for version "Falcon"


Running SU2......

-------------------------------------------------------------------------
|    ___ _   _ ___                                                      |
|   / __| | | |_  )   Release 6.2.0  "Falcon"                           |
|   \__ \ |_| |/ /                                                      |
|   |___/\___//___|   Suite (Computational Fluid Dynamics Code)         |
|                                                                       |
-------------------------------------------------------------------------
| The current SU2 release has been coordinated by the                   |
| SU2 International Developers Society <www.su2devsociety.org>          |
| with selected contributions from the open-source community.           |
-------------------------------------------------------------------------
| The main research teams contributing to the current release are:      |
| - Prof. Juan J. Alonso's group at Stanford University.                |
| - Prof. Piero Colonna's group at Delft University of Technology.      |
| - Prof. Nicolas R. Gauger's group at Kaiserslautern U. of Technology. |
| - Prof. Alberto Guardone's group at Polytechnic University of Milan.  |
| - Prof. Rafael Palacios' group at Imperial College London.            |
| - Prof. Vincent Terrapon's group at the University of Liege.          |
| - Prof. Edwin van der Weide's group at the University of Twente.      |
| - Lab. of New Concepts in Aeronautics at Tech. Inst. of Aeronautics.  |
-------------------------------------------------------------------------
| Copyright 2012-2019, Francisco D. Palacios, Thomas D. Economon,       |
|                      Tim Albring, and the SU2 contributors.           |
|                                                                       |
| SU2 is free software; you can redistribute it and/or                  |
| modify it under the terms of the GNU Lesser General Public            |
| License as published by the Free Software Foundation; either          |
| version 2.1 of the License, or (at your option) any later version.    |
|                                                                       |
| SU2 is distributed in the hope that it will be useful,                |
| but WITHOUT ANY WARRANTY; without even the implied warranty of        |
| MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU      |
| Lesser General Public License for more details.                       |
|                                                                       |
| You should have received a copy of the GNU Lesser General Public      |
| License along with SU2. If not, see <http://www.gnu.org/licenses/>.   |
-------------------------------------------------------------------------

------------------------ Physical Case Definition -----------------------
Compressible Euler equations.
Mach number: 0.294118.
Angle of attack (AoA): 0 deg, and angle of sideslip (AoS): 0 deg.
No restart solution, use the values at infinity (freestream).
Dimensional simulation.
The reference area is 10 m^2.
The semi-span will be computed using the max y(3D) value.
The reference length is 7.74597 m.
Reference origin for moment evaluation is (0.322749, 0, 0).
Surface(s) where the force coefficients are evaluated: 1.

Surface(s) plotted in the output file: 1.
Surface(s) affected by the design variables: 1.
Input mesh file name: aeroelasticIterative.su2

---------------------- Space Numerical Integration ----------------------
Roe (with entropy fix = 0.001) solver for the flow inviscid terms.
Roe with DDES's FD low-dissipation function.
Second order integration in space, with slope limiter.
Venkatakrishnan slope-limiting method, with constant: 0.05. 
The reference element size is: 1. 
Gradient computation using Green-Gauss theorem.

---------------------- Time Numerical Integration -----------------------
Local time stepping (steady state simulation).
Euler implicit method for the flow equations.
FGMRES is used for solving the linear system.
Using a ILU(0) preconditioning.
Convergence criteria of the linear solver: 1e-06.
Max number of linear iterations: 10.
V Multigrid Cycle, with 2 multigrid levels.
Damping factor for the residual restriction: 0.75.
Damping factor for the correction prolongation: 0.75.
No CFL adaptation.
+-------------------------------------------+
|  MG Level| Presmooth|PostSmooth|CorrectSmo|
+-------------------------------------------+
|         0|         1|         0|         0|
|         1|         2|         0|         0|
|         2|         3|         0|         0|
+-------------------------------------------+
Courant-Friedrichs-Lewy number:       10

------------------------- Convergence Criteria --------------------------
Maximum number of iterations: 5.
Reduce the density residual 6 orders of magnitude.
The minimum bound for the density residual is 10^(-8).
Start convergence criteria at iteration 10.

-------------------------- Output Information ---------------------------
Writing a solution file every 1000 iterations.
Writing the convergence history every 1 iterations.
The output file format is Tecplot ASCII (.dat).
Convergence history file name: history_aeroelasticIterative.
Forces breakdown file name: forces_breakdown_aeroelasticIterative.dat.
Surface flow coefficients file name: surface_flow_aeroelasticIterative.
Flow variables file name: flow_aeroelasticIterative.
Restart flow file name: restart_flow_aeroelasticIterative.dat.

------------------- Config File Boundary Information --------------------
+-----------------------------------------+
|         Marker Type|         Marker Name|
+-----------------------------------------+
|          Euler wall|                   1|
+-----------------------------------------+
|           Far-field|                   2|
+-----------------------------------------+

---------------------- Read Grid File Information -----------------------
Three dimensional problem.
81087 points.
2 surface markers.
+------------------------------------+
| Index|        Marker|      Elements|
+------------------------------------+
|     0|             1|         18026|
|     1|             2|           636|
+------------------------------------+
452128 tetrahedra.

------------------------- Geometry Preprocessing ------------------------
Setting point connectivity.
Renumbering points (Reverse Cuthill McKee Ordering).
Recomputing point connectivity.
Setting element connectivity.
Checking the numerical grid orientation.
Identifying edges and vertices.
Computing centers of gravity.
Setting the control volume structure.
Volume of the computational grid: 3.72e+06.
Finding max control volume width.
Searching for the closest normal neighbors to the surfaces.
Storing a mapping from global to local point index.
Compute the surface curvature.
Max K: 433. Mean K: 20.4. Standard deviation K: 49.2.
Checking for periodicity.
Setting the multigrid structure.
+-------------------------------------------+
|  MG Level|       CVs|Aggl. Rate|       CFL|
+-------------------------------------------+
|         0|     81087|    1/1.00|        10|
|         1|     13391|    1/6.06|      8.23|
|         2|      2049|    1/6.54|       6.6|
+-------------------------------------------+
Semi-span length = 3.87 m.
Wetted area = 20.6 m^2.
Area projection in the x-plane = 1.53 m^2, y-plane = 0.869 m^2, z-plane = 9.83 m^2.
Max. coordinate in the x-direction = 2.37 m, y-direction = 3.87 m, z-direction = 0.4 m.
Min coordinate in the x-direction = 0 m, y-direction = -3.87 m, z-direction = -0.0329 m.

------------------------- Driver information --------------------------
A Fluid driver has been instantiated.

------------------------ Iteration Preprocessing ------------------------
Zone 1: Euler/Navier-Stokes/RANS fluid iteration.

------------------------- Solver Preprocessing --------------------------
Inviscid flow: Computing density based on free-stream
temperature and pressure using the ideal gas law.
Force coefficients computed using free-stream values.

-- Models:
+------------------------------------------------------------------------------+
|          Viscosity Model|        Conductivity Model|              Fluid Model|
+------------------------------------------------------------------------------+
|                        -|                         -|             STANDARD_AIR|
+------------------------------------------------------------------------------+
-- Fluid properties:
+------------------------------------------------------------------------------+
|                  Name|    Dim. value|    Ref. value|      Unit|Non-dim. value|
+------------------------------------------------------------------------------+
|          Gas Constant|       287.058|             1|  N.m/kg.K|       287.058|
|      Spec. Heat Ratio|             -|             -|         -|           1.4|
+------------------------------------------------------------------------------+
-- Initial and free-stream conditions:
+------------------------------------------------------------------------------+
|                  Name|    Dim. value|    Ref. value|      Unit|Non-dim. value|
+------------------------------------------------------------------------------+
|       Static Pressure|        101325|             1|        Pa|        101325|
|               Density|       1.22498|             1|    kg/m^3|       1.22498|
|           Temperature|        288.15|             1|         K|        288.15|
|          Total Energy|        211798|             1|   m^2/s^2|        211798|
|            Velocity-X|       100.087|             1|       m/s|       100.087|
|            Velocity-Y|             0|             1|       m/s|             0|
|            Velocity-Z|             0|             1|       m/s|             0|
|    Velocity Magnitude|       100.087|             1|       m/s|       100.087|
+------------------------------------------------------------------------------+
|           Mach Number|             -|             -|         -|      0.294118|
+------------------------------------------------------------------------------+
Initialize Jacobian structure (Euler). MG level: 0.
Initialize Jacobian structure (Euler). MG level: 1.
Initialize Jacobian structure (Euler). MG level: 2.

----------------- Integration and Numerics Preprocessing ----------------
Integration Preprocessing.
Numerics Preprocessing.

---------------------- Python Interface Preprocessing ---------------------
Setting customized boundary conditions for zone 0

------------------------------ Begin Solver -----------------------------

------------------------ Evaluate Special Output ------------------------
Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat).
-------------------------------------------------------------------------


---------------------- Local Time Stepping Summary ----------------------
MG level: 0 -> Min. DT: 4.75954e-05. Max. DT: 0.133844. CFL: 10.
MG level: 1 -> Min. DT: 9.01528e-05. Max. DT: 0.192401. CFL: 8.2296.
MG level: 2 -> Min. DT: 0.000145445. Max. DT: 0.249416. CFL: 6.60257.
-------------------------------------------------------------------------

----------------------- Residual Evolution Summary ----------------------
log10[Maximum residual]: -0.734914.
Maximum residual point 2283, located at (1.25039, -0.895465, 0.208146).
-------------------------------------------------------------------------

 Iter    Time(s)     Res[Rho]     Res[RhoE]      CL(Total)      CD(Total)
    0   7.047631    -1.764585      3.704520      -0.192437       0.438788
    1   7.439931    -1.665379      3.813117       0.033126       0.242902
    2   7.429296    -1.655562      3.824904       0.168188       0.077505
    3   7.506399    -1.751945      3.727511       0.205416       0.022590

------------------------ Evaluate Special Output ------------------------
Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat).
-------------------------------------------------------------------------

    4   7.515930    -1.820189      3.650994       0.209024       0.012775

----------------------------- Solver Exit -------------------------------
Maximum number of external iterations reached (EXT_ITER).
-------------------------------------------------------------------------

-------------------------- File Output Summary --------------------------
Writing comma-separated values (CSV) surface files.
Loading solution output data locally on each rank.
Sorting output data across all ranks.
Writing binary SU2 native restart file.
Preparing element connectivity across all ranks.
Writing Tecplot ASCII file volume solution file.
Writing Tecplot ASCII file surface solution file.
-------------------------------------------------------------------------


------------------------- Solver Postprocessing -------------------------
Deleted CNumerics container.
Deleted CIntegration container.
Deleted CSolver container.
Deleted CIteration container.
Deleted CInterpolator container.
Deleted CTransfer container.
Deleted CGeometry container.
Deleted CFreeFormDefBox class.
Deleted CSurfaceMovement class.
Deleted CVolumetricMovement class.
Deleted CConfig container.
Deleted nInst container.
Deleted COutput class.
-------------------------------------------------------------------------

------------------------- Exit Success (SU2_CFD) ------------------------


==> Running SU2 post-analysis...
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
	Number of variables = 7
	Number of data points = 9015
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
	Number of variables = 7
	Number of data points = 9015
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
	Number of variables = 7
	Number of data points = 9015
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
	Number of variables = 7
	Number of data points = 9015


Executing dataTransfer "Pressure"......
Bound upperWing: Normalized Integrated Pressure
  Rank=0: src=6.265700e+09, tgt=6.265700e+09, diff=3.835140e+01
Bound lowerWing: Normalized Integrated Pressure
  Rank=0: src=6.102777e+09, tgt=6.102777e+09, diff=1.295066e+01
Bound leftTip: Normalized Integrated Pressure
  Rank=0: src=6.123320e+07, tgt=6.123320e+07, diff=0.000000e+00
Bound riteTip: Normalized Integrated Pressure
  Rank=0: src=6.125526e+07, tgt=6.125526e+07, diff=0.000000e+00

==> Running ASTROS pre-analysis...

Getting FEA materials.......
	Number of materials - 2
	Material name - Unobtainium
	No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic"
	Material name - Madeupium
	Done getting FEA materials

Getting FEA properties.......
	Number of properties - 5
	Property name - leftWingSkin
	Property name - riteWingSkin
	Property name - wingRib
	Property name - wingSpar1
	Property name - wingSpar2
	Done getting FEA properties
Updating mesh element types based on properties input

Getting FEA constraints.......
	Number of constraints - 1
	Constraint name - rootConstraint
	No "constraintType" specified for Constraint tuple rootConstraint, defaulting to "ZeroDisplacement"
	Done getting FEA constraints
Support tuple is NULL - No supports applied
Connect tuple is NULL - Using defaults

Getting FEA loads.......
	Number of loads - 1
	Load name - pressureAero
	No "groupName" specified for Load tuple pressureAero, going to use load name
	Done getting FEA loads
Extracting external pressure loads from data transfer....
	TransferName = upperWing
	Number of Elements = 96 (total = 96)
	TransferName = lowerWing
	Number of Elements = 96 (total = 192)
	TransferName = leftTip
	Number of Elements = 10 (total = 202)
	TransferName = riteTip
	Number of Elements = 10 (total = 212)
Design_Variable tuple is NULL - No design variables applied
Design_Constraint tuple is NULL - No design constraints applied
Analysis tuple is NULL

Getting FEA analyses.......
	Number of analyses - 1
	Analysis name - Default
	Done getting FEA analyses

Writing Astros grid and connectivity file (in large field format) ....
Finished writing Astros grid file

Writing subElement types (if any) - appending mesh file

Writing Astros instruction file....
	Writing analysis cards
	Writing load ADD cards
	Writing constraint cards--each subcase individually
	Writing load cards
	Writing material cards
	Writing property cards
	Writing coordinate system cards


Running Astros......

==> Running ASTROS post-analysis...


Executing dataTransfer "Displacement"......

==> Running SU2 pre-analysis...
Getting CFD boundary conditions
	Boundary condition name - Wing
	Boundary condition name - Farfield
	Done getting CFD boundary conditions
Found link for volume mesh (Volume_Mesh) from parent
Writing boundary flags
 - bcProps.surfaceProp[0].surfaceType = 1
 - bcProps.surfaceProp[1].surfaceType = 3
Done boundary flags
Writing SU2 data transfer files
Writing SU2 Motion File - aeroelasticIterative_motion.dat
Warning: The su2 cfg file will be overwritten!
Write SU2 configuration file for version "Falcon"


Running SU2......

-------------------------------------------------------------------------
|    ___ _   _ ___                                                      |
|   / __| | | |_  )   Release 6.2.0  "Falcon"                           |
|   \__ \ |_| |/ /                                                      |
|   |___/\___//___|   Suite (Mesh Deformation Code)                     |
|                                                                       |
-------------------------------------------------------------------------
| The current SU2 release has been coordinated by the                   |
| SU2 International Developers Society <www.su2devsociety.org>          |
| with selected contributions from the open-source community.           |
-------------------------------------------------------------------------
| The main research teams contributing to the current release are:      |
| - Prof. Juan J. Alonso's group at Stanford University.                |
| - Prof. Piero Colonna's group at Delft University of Technology.      |
| - Prof. Nicolas R. Gauger's group at Kaiserslautern U. of Technology. |
| - Prof. Alberto Guardone's group at Polytechnic University of Milan.  |
| - Prof. Rafael Palacios' group at Imperial College London.            |
| - Prof. Vincent Terrapon's group at the University of Liege.          |
| - Prof. Edwin van der Weide's group at the University of Twente.      |
| - Lab. of New Concepts in Aeronautics at Tech. Inst. of Aeronautics.  |
-------------------------------------------------------------------------
| Copyright 2012-2019, Francisco D. Palacios, Thomas D. Economon,       |
|                      Tim Albring, and the SU2 contributors.           |
|                                                                       |
| SU2 is free software; you can redistribute it and/or                  |
| modify it under the terms of the GNU Lesser General Public            |
| License as published by the Free Software Foundation; either          |
| version 2.1 of the License, or (at your option) any later version.    |
|                                                                       |
| SU2 is distributed in the hope that it will be useful,                |
| but WITHOUT ANY WARRANTY; without even the implied warranty of        |
| MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU      |
| Lesser General Public License for more details.                       |
|                                                                       |
| You should have received a copy of the GNU Lesser General Public      |
| License along with SU2. If not, see <http://www.gnu.org/licenses/>.   |
-------------------------------------------------------------------------

------------------------ Physical Case Definition -----------------------
Input mesh file name: aeroelasticIterative.su2

---------------------- Grid deformation parameters ----------------------
Grid deformation using a linear elasticity method.


-------------------------- Output Information ---------------------------
Output mesh file name: aeroelasticIterative.su2. 
A file will be created to visualize the surface deformation.
No file for visualizing the deformation.
Cell stiffness scaled by distance to nearest solid surface.

------------------- Config File Boundary Information --------------------
+-----------------------------------------+
|         Marker Type|         Marker Name|
+-----------------------------------------+
|          Euler wall|                   1|
+-----------------------------------------+
|           Far-field|                   2|
+-----------------------------------------+

---------------------- Read Grid File Information -----------------------
Three dimensional problem.
81087 points.
2 surface markers.
+------------------------------------+
| Index|        Marker|      Elements|
+------------------------------------+
|     0|             1|         18026|
|     1|             2|           636|
+------------------------------------+
452128 tetrahedra.

----------------------- Preprocessing computations ----------------------
Setting local point connectivity.
Checking the numerical grid orientation of the interior elements.
Identify edges and vertices.
Computing centers of gravity.
Setting the bound control volume structure.
Merging grid connectivity.
Merging grid coordinates.
Writing surface mesh file.
Writing .csv surface file.

--------------------- Surface grid deformation (ZONE 0) -----------------
Performing the deformation of the surface grid.
Updating the surface coordinates from the input file.

------------------- Volumetric grid deformation (ZONE 0) ----------------
Performing the deformation of the volumetric grid.
Computing volumes of the grid elements.
Min. volume: 1.30476e-06, max. volume: 4674.72.
Min. distance: 0.0169992, max. distance: 132.146.

# ILU preconditioner.

# FGMRES residual history
# Residual tolerance target = 1e-14
# Initial residual norm     = 9.15648
     0     1
     10     0.00155825
     20     3.18889e-05
     30     3.50673e-06
     40     5.8781e-07
     50     6.3065e-08
     60     2.96694e-09
     70     1.19673e-10
     80     4.53477e-12
     90     1.70036e-13
     100     2.86062e-14
     110     2.816e-14
     120     2.81594e-14
     130     2.81594e-14
     140     2.81594e-14
     150     2.81594e-14
     160     2.81594e-14
     170     2.8136e-14
     180     1.35735e-14
# FGMRES final (true) residual:
# Iteration = 182: |res|/|res0| = 7.74374e-15.

Computing volumes of the grid elements.
Non-linear iter.: 1/3. Linear iter.: 182. Min. volume: 1.25578. Error: 7.09054e-14.
Computing volumes of the grid elements.
Min. volume: 1.25578, max. volume: 4.73428e+10.
Min. distance: 4.409, max. distance: 12952.3.

# ILU preconditioner.

# FGMRES residual history
# Residual tolerance target = 1e-14
# Initial residual norm     = 91994.7
     0     1
     10     0.00734772
     20     0.00562794
     30     0.00448978
     40     0.0025112
     50     0.00211445
     60     0.0016828
     70     0.00160343
     80     0.00146444
     90     0.00141096
     100     0.00132886
     110     0.00128244
     120     0.00126405
     130     0.00121126
     140     0.00116279
     150     0.00101357
     160     0.000867317
     170     0.000768805
     180     0.000705568
     190     0.000669162
     200     0.000626613
     210     0.000535373
     220     0.000473201
     230     0.000412394
     240     0.000375247
     250     0.000356338
     260     0.000302262
     270     0.000261247
     280     0.000232062
     290     0.0002104
     300     0.000189482
     310     0.000160919
     320     0.00014318
     330     0.000129237
     340     0.000117224
     350     0.000103776
     360     9.54904e-05
     370     8.94594e-05
     380     8.74119e-05
     390     8.51446e-05
     400     8.27319e-05
     410     7.96882e-05
     420     7.53906e-05
     430     7.38432e-05
     440     7.18947e-05
     450     7.03021e-05
     460     6.77425e-05
     470     6.48965e-05
     480     6.19719e-05
     490     5.73459e-05
     500     5.57488e-05
# FGMRES final (true) residual:
# Iteration = 500: |res|/|res0| = 5.57488e-05.

# WARNING in CSysSolve::FGMRES_LinSolver(): 
# true residual norm and calculated residual norm do not agree.
# res = 5.12859, beta = 5.12859, tol = 1e-13.
# res - beta = 8.17577e-11

Computing volumes of the grid elements.
Non-linear iter.: 2/3. Linear iter.: 500. Min. volume: 5.15423. Error: 5.12859.
Computing volumes of the grid elements.
Min. volume: 5.15423, max. volume: 3.73141e+12.
Min. distance: 7.03807, max. distance: 72290.5.

# ILU preconditioner.

# FGMRES residual history
# Residual tolerance target = 1e-14
# Initial residual norm     = 149485
     0     1
     10     0.00548596
     20     0.00206638
     30     0.00200579
     40     0.00193331
     50     0.00179781
     60     0.00168381
     70     0.00134777
     80     0.00118803
     90     0.00106996
     100     0.000857073
     110     0.000712221
     120     0.000605828
     130     0.000527313
     140     0.000471176
     150     0.000437766
     160     0.000389888
     170     0.000347891
     180     0.000319542
     190     0.000302576
     200     0.00028891
     210     0.000272393
     220     0.000254702
     230     0.000243022
     240     0.000233567
     250     0.000226707
     260     0.000217414
     270     0.000204045
     280     0.000184671
     290     0.00017227
     300     0.000159396
     310     0.000145279
     320     0.000129636
     330     0.000120155
     340     0.000113431
     350     0.000107013
     360     0.000102719
     370     9.88463e-05
     380     9.46353e-05
     390     8.9677e-05
     400     8.39651e-05
     410     7.61227e-05
     420     6.92151e-05
     430     6.44504e-05
     440     6.14585e-05
     450     5.9322e-05
     460     5.79298e-05
     470     5.53719e-05
     480     5.39679e-05
     490     5.22408e-05
     500     5.06309e-05
# FGMRES final (true) residual:
# Iteration = 500: |res|/|res0| = 5.06309e-05.

# WARNING in CSysSolve::FGMRES_LinSolver(): 
# true residual norm and calculated residual norm do not agree.
# res = 7.56854, beta = 7.56854, tol = 1e-13.
# res - beta = -4.43197e-10

Computing volumes of the grid elements.
Non-linear iter.: 3/3. Linear iter.: 500. Min. volume: 5.32157. Error: 7.56854.

----------------------- Write deformed grid files -----------------------
Merging grid connectivity.
Merging grid coordinates.
Writing surface mesh file.
Writing .su2 file.
Writing .stl surface file.
Writing .csv surface file.
Adding any FFD information to the SU2 file.

------------------------- Solver Postprocessing -------------------------
Deleted CGeometry container.
Deleted CSurfaceMovement class.
Deleted CVolumetricMovement class.
Deleted CConfig container.
Deleted COutput class.

Completed in 233.135231 seconds on 1 core.

------------------------- Exit Success (SU2_DEF) ------------------------


-------------------------------------------------------------------------
|    ___ _   _ ___                                                      |
|   / __| | | |_  )   Release 6.2.0  "Falcon"                           |
|   \__ \ |_| |/ /                                                      |
|   |___/\___//___|   Suite (Computational Fluid Dynamics Code)         |
|                                                                       |
-------------------------------------------------------------------------
| The current SU2 release has been coordinated by the                   |
| SU2 International Developers Society <www.su2devsociety.org>          |
| with selected contributions from the open-source community.           |
-------------------------------------------------------------------------
| The main research teams contributing to the current release are:      |
| - Prof. Juan J. Alonso's group at Stanford University.                |
| - Prof. Piero Colonna's group at Delft University of Technology.      |
| - Prof. Nicolas R. Gauger's group at Kaiserslautern U. of Technology. |
| - Prof. Alberto Guardone's group at Polytechnic University of Milan.  |
| - Prof. Rafael Palacios' group at Imperial College London.            |
| - Prof. Vincent Terrapon's group at the University of Liege.          |
| - Prof. Edwin van der Weide's group at the University of Twente.      |
| - Lab. of New Concepts in Aeronautics at Tech. Inst. of Aeronautics.  |
-------------------------------------------------------------------------
| Copyright 2012-2019, Francisco D. Palacios, Thomas D. Economon,       |
|                      Tim Albring, and the SU2 contributors.           |
|                                                                       |
| SU2 is free software; you can redistribute it and/or                  |
| modify it under the terms of the GNU Lesser General Public            |
| License as published by the Free Software Foundation; either          |
| version 2.1 of the License, or (at your option) any later version.    |
|                                                                       |
| SU2 is distributed in the hope that it will be useful,                |
| but WITHOUT ANY WARRANTY; without even the implied warranty of        |
| MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU      |
| Lesser General Public License for more details.                       |
|                                                                       |
| You should have received a copy of the GNU Lesser General Public      |
| License along with SU2. If not, see <http://www.gnu.org/licenses/>.   |
-------------------------------------------------------------------------

------------------------ Physical Case Definition -----------------------
Compressible Euler equations.
Mach number: 0.294118.
Angle of attack (AoA): 0 deg, and angle of sideslip (AoS): 0 deg.
No restart solution, use the values at infinity (freestream).
Dimensional simulation.
The reference area is 10 m^2.
The semi-span will be computed using the max y(3D) value.
The reference length is 7.74597 m.
Reference origin for moment evaluation is (0.322749, 0, 0).
Surface(s) where the force coefficients are evaluated: 1.

Surface(s) plotted in the output file: 1.
Surface(s) affected by the design variables: 1.
Input mesh file name: aeroelasticIterative.su2

---------------------- Space Numerical Integration ----------------------
Roe (with entropy fix = 0.001) solver for the flow inviscid terms.
Roe with DDES's FD low-dissipation function.
Second order integration in space, with slope limiter.
Venkatakrishnan slope-limiting method, with constant: 0.05. 
The reference element size is: 1. 
Gradient computation using Green-Gauss theorem.

---------------------- Time Numerical Integration -----------------------
Local time stepping (steady state simulation).
Euler implicit method for the flow equations.
FGMRES is used for solving the linear system.
Using a ILU(0) preconditioning.
Convergence criteria of the linear solver: 1e-06.
Max number of linear iterations: 10.
V Multigrid Cycle, with 2 multigrid levels.
Damping factor for the residual restriction: 0.75.
Damping factor for the correction prolongation: 0.75.
No CFL adaptation.
+-------------------------------------------+
|  MG Level| Presmooth|PostSmooth|CorrectSmo|
+-------------------------------------------+
|         0|         1|         0|         0|
|         1|         2|         0|         0|
|         2|         3|         0|         0|
+-------------------------------------------+
Courant-Friedrichs-Lewy number:       10

------------------------- Convergence Criteria --------------------------
Maximum number of iterations: 5.
Reduce the density residual 6 orders of magnitude.
The minimum bound for the density residual is 10^(-8).
Start convergence criteria at iteration 10.

-------------------------- Output Information ---------------------------
Writing a solution file every 1000 iterations.
Writing the convergence history every 1 iterations.
The output file format is Tecplot ASCII (.dat).
Convergence history file name: history_aeroelasticIterative.
Forces breakdown file name: forces_breakdown_aeroelasticIterative.dat.
Surface flow coefficients file name: surface_flow_aeroelasticIterative.
Flow variables file name: flow_aeroelasticIterative.
Restart flow file name: restart_flow_aeroelasticIterative.dat.

------------------- Config File Boundary Information --------------------
+-----------------------------------------+
|         Marker Type|         Marker Name|
+-----------------------------------------+
|          Euler wall|                   1|
+-----------------------------------------+
|           Far-field|                   2|
+-----------------------------------------+

---------------------- Read Grid File Information -----------------------
Three dimensional problem.
81087 points.
2 surface markers.
+------------------------------------+
| Index|        Marker|      Elements|
+------------------------------------+
|     0|             1|         18026|
|     1|             2|           636|
+------------------------------------+
452128 tetrahedra.

------------------------- Geometry Preprocessing ------------------------
Setting point connectivity.
Renumbering points (Reverse Cuthill McKee Ordering).
Recomputing point connectivity.
Setting element connectivity.
Checking the numerical grid orientation.
There has been a re-orientation of the TETRAHEDRON volume elements.
There has been a re-orientation of the TRIANGLE surface elements.
Identifying edges and vertices.
Computing centers of gravity.
Setting the control volume structure.
Volume of the computational grid: 2.77e+16.
Finding max control volume width.
Searching for the closest normal neighbors to the surfaces.
Storing a mapping from global to local point index.
Compute the surface curvature.
Max K: 2.54. Mean K: 0.0074. Standard deviation K: 0.049.
Checking for periodicity.
Setting the multigrid structure.
+-------------------------------------------+
|  MG Level|       CVs|Aggl. Rate|       CFL|
+-------------------------------------------+
|         0|     81087|    1/1.00|        10|
|         1|     13387|    1/6.06|      8.23|
|         2|      2086|    1/6.42|      6.64|
+-------------------------------------------+
Semi-span length = 3.16e+04 m.
Wetted area = 2.04e+10 m^2.
Area projection in the x-plane = 8.67e+09 m^2, y-plane = 6.34e+09 m^2, z-plane = 5.99e+08 m^2.
Max. coordinate in the x-direction = 1.43e+03 m, y-direction = 3.16e+04 m, z-direction = 0.168 m.
Min coordinate in the x-direction = -1.5e+04 m, y-direction = -3.31e+04 m, z-direction = -3.63e+05 m.

------------------------- Driver information --------------------------
A Fluid driver has been instantiated.

------------------------ Iteration Preprocessing ------------------------
Zone 1: Euler/Navier-Stokes/RANS fluid iteration.

------------------------- Solver Preprocessing --------------------------
Inviscid flow: Computing density based on free-stream
temperature and pressure using the ideal gas law.
Force coefficients computed using free-stream values.

-- Models:
+------------------------------------------------------------------------------+
|          Viscosity Model|        Conductivity Model|              Fluid Model|
+------------------------------------------------------------------------------+
|                        -|                         -|             STANDARD_AIR|
+------------------------------------------------------------------------------+
-- Fluid properties:
+------------------------------------------------------------------------------+
|                  Name|    Dim. value|    Ref. value|      Unit|Non-dim. value|
+------------------------------------------------------------------------------+
|          Gas Constant|       287.058|             1|  N.m/kg.K|       287.058|
|      Spec. Heat Ratio|             -|             -|         -|           1.4|
+------------------------------------------------------------------------------+
-- Initial and free-stream conditions:
+------------------------------------------------------------------------------+
|                  Name|    Dim. value|    Ref. value|      Unit|Non-dim. value|
+------------------------------------------------------------------------------+
|       Static Pressure|        101325|             1|        Pa|        101325|
|               Density|       1.22498|             1|    kg/m^3|       1.22498|
|           Temperature|        288.15|             1|         K|        288.15|
|          Total Energy|        211798|             1|   m^2/s^2|        211798|
|            Velocity-X|       100.087|             1|       m/s|       100.087|
|            Velocity-Y|             0|             1|       m/s|             0|
|            Velocity-Z|             0|             1|       m/s|             0|
|    Velocity Magnitude|       100.087|             1|       m/s|       100.087|
+------------------------------------------------------------------------------+
|           Mach Number|             -|             -|         -|      0.294118|
+------------------------------------------------------------------------------+
Initialize Jacobian structure (Euler). MG level: 0.
Initialize Jacobian structure (Euler). MG level: 1.
Initialize Jacobian structure (Euler). MG level: 2.

----------------- Integration and Numerics Preprocessing ----------------
Integration Preprocessing.
Numerics Preprocessing.

---------------------- Python Interface Preprocessing ---------------------
Setting customized boundary conditions for zone 0

------------------------------ Begin Solver -----------------------------

------------------------ Evaluate Special Output ------------------------
Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat).
-------------------------------------------------------------------------


---------------------- Local Time Stepping Summary ----------------------
MG level: 0 -> Min. DT: 0.000131617. Max. DT: 400.624. CFL: 10.
MG level: 1 -> Min. DT: 0.0481787. Max. DT: 587.302. CFL: 8.22878.
MG level: 2 -> Min. DT: 0.14467. Max. DT: 698.218. CFL: 6.64207.
-------------------------------------------------------------------------

----------------------- Residual Evolution Summary ----------------------
log10[Maximum residual]: 12.1487.
Maximum residual point 34103, located at (153967, 82285.4, -203576).
There are 5869 non-physical points in the solution.
-------------------------------------------------------------------------

 Iter    Time(s)     Res[Rho]     Res[RhoE]      CL(Total)      CD(Total)
    0   7.304607    10.314447     15.783553  -10000.000000   10000.000000
    1   7.516312    10.956724     16.663628  -10000.000000   10000.000000
    2   7.515704    11.082252     16.968784  -10000.000000  -10000.000000
    3   7.571443    11.368463     17.483368  -10000.000000   10000.000000

------------------------ Evaluate Special Output ------------------------
Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat).
-------------------------------------------------------------------------

    4   7.581103    11.556319     17.680648  -10000.000000   10000.000000

----------------------------- Solver Exit -------------------------------
Maximum number of external iterations reached (EXT_ITER).
-------------------------------------------------------------------------

-------------------------- File Output Summary --------------------------
Writing comma-separated values (CSV) surface files.
Loading solution output data locally on each rank.
Sorting output data across all ranks.
Writing binary SU2 native restart file.
Preparing element connectivity across all ranks.
Writing Tecplot ASCII file volume solution file.
Writing Tecplot ASCII file surface solution file.
-------------------------------------------------------------------------

Warning: there are 27384 non-physical points in the solution.
Warning: 2373 reconstructed states for upwinding are non-physical.

------------------------- Solver Postprocessing -------------------------
Deleted CNumerics container.
Deleted CIntegration container.
Deleted CSolver container.
Deleted CIteration container.
Deleted CInterpolator container.
Deleted CTransfer container.
Deleted CGeometry container.
Deleted CFreeFormDefBox class.
Deleted CSurfaceMovement class.
Deleted CVolumetricMovement class.
Deleted CConfig container.
Deleted nInst container.
Deleted COutput class.
-------------------------------------------------------------------------

------------------------- Exit Success (SU2_CFD) ------------------------


==> Running SU2 post-analysis...
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
	Number of variables = 7
	Number of data points = 9015
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
	Number of variables = 7
	Number of data points = 9015
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
	Number of variables = 7
	Number of data points = 9015
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
	Number of variables = 7
	Number of data points = 9015


Executing dataTransfer "Pressure"......
Bound upperWing: Normalized Integrated Pressure
  Rank=0: src=3.952649e+10, tgt=3.952648e+10, diff=6.054567e+02
Bound lowerWing: Normalized Integrated Pressure
  Rank=0: src=1.983030e+10, tgt=1.983030e+10, diff=8.194724e+02
Bound leftTip: Normalized Integrated Pressure
  Rank=0: src=1.856825e+08, tgt=1.856825e+08, diff=3.707409e-05
Bound riteTip: Normalized Integrated Pressure
  Rank=0: src=7.116292e+08, tgt=7.116292e+08, diff=0.000000e+00

==> Running ASTROS pre-analysis...

Getting FEA materials.......
	Number of materials - 2
	Material name - Unobtainium
	No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic"
	Material name - Madeupium
	Done getting FEA materials

Getting FEA properties.......
	Number of properties - 5
	Property name - leftWingSkin
	Property name - riteWingSkin
	Property name - wingRib
	Property name - wingSpar1
	Property name - wingSpar2
	Done getting FEA properties
Updating mesh element types based on properties input

Getting FEA constraints.......
	Number of constraints - 1
	Constraint name - rootConstraint
	No "constraintType" specified for Constraint tuple rootConstraint, defaulting to "ZeroDisplacement"
	Done getting FEA constraints
Support tuple is NULL - No supports applied
Connect tuple is NULL - Using defaults

Getting FEA loads.......
	Number of loads - 1
	Load name - pressureAero
	No "groupName" specified for Load tuple pressureAero, going to use load name
	Done getting FEA loads
Extracting external pressure loads from data transfer....
	TransferName = upperWing
	Number of Elements = 96 (total = 96)
	TransferName = lowerWing
	Number of Elements = 96 (total = 192)
	TransferName = leftTip
	Number of Elements = 10 (total = 202)
	TransferName = riteTip
	Number of Elements = 10 (total = 212)
Design_Variable tuple is NULL - No design variables applied
Design_Constraint tuple is NULL - No design constraints applied
Analysis tuple is NULL

Getting FEA analyses.......
	Number of analyses - 1
	Analysis name - Default
	Done getting FEA analyses

Writing Astros grid and connectivity file (in large field format) ....
Finished writing Astros grid file

Writing subElement types (if any) - appending mesh file

Writing Astros instruction file....
	Writing analysis cards
	Writing load ADD cards
	Writing constraint cards--each subcase individually
	Writing load cards
	Writing material cards
	Writing property cards
	Writing coordinate system cards


Running Astros......

==> Running ASTROS post-analysis...
--> temporary directory "tmp_OpenCSM_00" removed
 Cleaning up aflr4Instance - 0
 Cleaning up aflr3Instance - 0
 Cleaning up su2Instance - 0
 Cleaning up egadsInstance - 0
 Cleaning up astrosInstance - 0
 EGADS Info: 762 Objects, 1223 Reference in Use (of 29696) at Close!

real	7m27.670s
user	7m6.427s
sys	0m10.125s
+ status=0
+ set +x

=================================================
data/session11/aeroelastic_Iterative_SU2_Astros.py passed (as expected)
=================================================


*************************************************
*************************************************


All tests pass!


=================================================
=================================================
[Execution node] check if [macys] is in [[windows10x64, windows7x64]]
Run condition [Execution node ] preventing perform for step [Execute Windows batch command]
[GNU C Compiler (gcc)] Sleeping for 5 seconds due to JENKINS-32191...
[GNU C Compiler (gcc)] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_QuickTestCaps/7.4/CAPS/training/DARWIN64')
[GNU C Compiler (gcc)] Successfully parsed console log
[GNU C Compiler (gcc)] -> found 0 issues (skipped 0 duplicates)
[GNU C Compiler (gcc)] Skipping post processing
[GNU C Compiler (gcc)] No filter has been set, publishing all 0 issues
[GNU C Compiler (gcc)] Repository miner is not configured, skipping mining
[Clang (LLVM based)] Sleeping for 5 seconds due to JENKINS-32191...
[Clang (LLVM based)] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_QuickTestCaps/7.4/CAPS/training/DARWIN64')
[Clang (LLVM based)] Successfully parsed console log
[Clang (LLVM based)] -> found 0 issues (skipped 0 duplicates)
[Clang (LLVM based)] Skipping post processing
[Clang (LLVM based)] No filter has been set, publishing all 0 issues
[Clang (LLVM based)] Repository miner is not configured, skipping mining
[Static Analysis] Reference build recorder is not configured
[Static Analysis] Obtaining reference build from same job (7.4,DARWIN64,macys)
[Static Analysis] Using reference build 'ESP_QuickTestCaps/CASREV=7.4,ESP_ARCH=DARWIN64,buildnode=macys #23' to compute new, fixed, and outstanding issues
[Static Analysis] Issues delta (vs. reference build): outstanding: 0, new: 0, fixed: 0
[Static Analysis] Evaluating quality gates
[Static Analysis] -> PASSED - Total (any severity): 0 - Quality QualityGate: 1
[Static Analysis] -> All quality gates have been passed
[Static Analysis] Health report is disabled - skipping
[Static Analysis] Created analysis result for 0 issues (found 0 new issues, fixed 0 issues)
[Static Analysis] Attaching ResultAction with ID 'analysis' to build 'ESP_QuickTestCaps/CASREV=7.4,ESP_ARCH=DARWIN64,buildnode=macys #24'.
[Checks API] No suitable checks publisher found.
[PostBuildScript] - [INFO] Executing post build scripts.
[PostBuildScript] - [INFO] build step #0 should only be executed on MATRIX
[WS-CLEANUP] Deleting project workspace...
[WS-CLEANUP] done
Finished: SUCCESS