Console Output

Skipping 3,566 KB.. Full Log
    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     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       0.003    0.0
    udprim                   14       0.445    0.2
    restore                  12       0.039    0.0
    rule                      1       0.093    0.0
    intersect                 4      42.911   20.9
    subtract                  1      41.099   20.0
    union                     1     119.505   58.2
    join                      1       0.149    0.1
    extract                   1       1.008    0.5
    translate                 2       0.019    0.0
    rotatex                   2       0.004    0.0
    rotatey                   1       0.002    0.0
    scale                     2       0.004    0.0
    mirror                    1       0.041    0.0
    interface                 4       0.000    0.0
    end                       4       0.000    0.0
    set                      77       0.002    0.0
    udparg                    3       0.000    0.0
    select                   26       0.073    0.0
    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     205.399
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: 1: nastran: 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	0m13.918s
user	0m53.028s
sys	2m33.536s
+ 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 /jenkins/workspace/ESP_QuickTestCaps/7.4/CAPS/training/LINUX64/CAPS/training/training.log
Definition of "au" in "/usr/share/xml/udunits/udunits2-accepted.xml", line 123, overrides prefixed-unit "1.6605402e-45 kilogram"
Definition of "kt" in "/usr/share/xml/udunits/udunits2-common.xml", line 105, overrides prefixed-unit "1000000 kilogram"
Definition of "microns" in "/usr/share/xml/udunits/udunits2-common.xml", line 397, overrides prefixed-unit "1e-15 second"
Definition of "ft" in "/usr/share/xml/udunits/udunits2-common.xml", line 508, overrides prefixed-unit "1e-12 kilogram"
Definition of "yd" in "/usr/share/xml/udunits/udunits2-common.xml", line 517, overrides prefixed-unit "8.64e-20 second"
Definition of "pt" in "/usr/share/xml/udunits/udunits2-common.xml", line 771, overrides prefixed-unit "1e-09 kilogram"
Definition of "at" in "/usr/share/xml/udunits/udunits2-common.xml", line 1236, overrides prefixed-unit "1e-15 kilogram"
Definition of "ph" in "/usr/share/xml/udunits/udunits2-common.xml", line 1866, overrides prefixed-unit "3.6e-09 second"
Definition of "nt" in "/usr/share/xml/udunits/udunits2-common.xml", line 1875, 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       0.533    0.3
    restore                  10       0.046    0.0
    rule                      1       0.057    0.0
    intersect                 1      38.085   20.4
    subtract                  1      34.305   18.4
    union                     1     112.474   60.3
    join                      1       0.096    0.1
    extract                   1       0.673    0.4
    translate                 2       0.015    0.0
    rotatex                   2       0.003    0.0
    rotatey                   1       0.001    0.0
    scale                     2       0.003    0.0
    mirror                    1       0.026    0.0
    interface                 5       0.000    0.0
    end                       5       0.000    0.0
    set                      93       0.002    0.0
    udparg                    3       0.000    0.0
    select                   28       0.116    0.1
    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     186.436
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     Linux 3.10.0-957.27.2.el7.x86_64 x86_64
AFLR2    : Compile Date   10/12/20 @ 12:16PM
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     Linux 3.10.0-957.27.2.el7.x86_64 x86_64
AFLR4    : Compile Date   10/30/20 @ 04:17PM
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          =     0.378   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     Linux 3.10.0-957.27.2.el7.x86_64 x86_64
AFLR3    : Compile Date   10/12/20 @ 12:16PM
AFLR3    : Copyright 1994-2020, D.L. Marcum
AFLR3    : ---------------------------------------
 
AFLR3 IC : INPUT SURFACE GRID CHECK
 
AFLR3 IC : Nodes, Elements   =      9335         0
 
AFLR3    : CPU Time          =     0.030   seconds
 
AFLR3 IG : INITIAL VOLUME GRID GENERATION
 
AFLR3 IG : Nodes, Elements   =      9335         0
AFLR3 IG : Nodes, Elements   =         8        10
AFLR3 IG : Nodes, Elements   =      1868     12786
AFLR3 IG : Nodes, Elements   =      3736     26150
AFLR3 IG : Nodes, Elements   =      5604     39927
AFLR3 IG : Nodes, Elements   =      7472     54611
AFLR3 IG : Nodes, Elements   =      9340     70118
AFLR3 IG : Nodes, Elements   =      9342     70165
AFLR3 IG : Nodes, Elements   =      9342     69975
AFLR3 IG : Nodes, Elements   =      9335     42825
AFLR3 IG : Nodes, Elements   =      9335     42887
AFLR3 IG : Nodes, Elements   =      9335     30508
AFLR3 IG : Nodes, Elements   =      9335     28544
 
AFLR3    : CPU Time          =     0.379   seconds
 
AFLR3 GG : ISOTROPIC VOLUME GRID GENERATION
 
AFLR3 GG : Nodes, Elements   =      9335     28544
AFLR3 GG : Nodes, Elements   =     13605     41435
AFLR3 GG : Nodes, Elements   =     13605     58556
AFLR3 GG : Nodes, Elements   =     13605     53947
AFLR3 GG : Nodes, Elements   =     17189     65130
AFLR3 GG : Nodes, Elements   =     17189     79156
AFLR3 GG : Nodes, Elements   =     17189     74514
AFLR3 GG : Nodes, Elements   =     20729     85484
AFLR3 GG : Nodes, Elements   =     20729     99069
AFLR3 GG : Nodes, Elements   =     20729     95071
AFLR3 GG : Nodes, Elements   =     24382    106151
AFLR3 GG : Nodes, Elements   =     24382    120923
AFLR3 GG : Nodes, Elements   =     24382    116866
AFLR3 GG : Nodes, Elements   =     28114    128178
AFLR3 GG : Nodes, Elements   =     28114    142576
AFLR3 GG : Nodes, Elements   =     28114    138732
AFLR3 GG : Nodes, Elements   =     31784    149831
AFLR3 GG : Nodes, Elements   =     31784    164352
AFLR3 GG : Nodes, Elements   =     31784    160601
AFLR3 GG : Nodes, Elements   =     35325    171295
AFLR3 GG : Nodes, Elements   =     35325    185141
AFLR3 GG : Nodes, Elements   =     35325    181584
AFLR3 GG : Nodes, Elements   =     38840    192176
AFLR3 GG : Nodes, Elements   =     38840    205878
AFLR3 GG : Nodes, Elements   =     38840    202404
AFLR3 GG : Nodes, Elements   =     42161    212408
AFLR3 GG : Nodes, Elements   =     42161    225341
AFLR3 GG : Nodes, Elements   =     42161    222111
AFLR3 GG : Nodes, Elements   =     45354    231715
AFLR3 GG : Nodes, Elements   =     45354    244201
AFLR3 GG : Nodes, Elements   =     45354    240964
AFLR3 GG : Nodes, Elements   =     48413    250161
AFLR3 GG : Nodes, Elements   =     48413    262176
AFLR3 GG : Nodes, Elements   =     48413    259161
AFLR3 GG : Nodes, Elements   =     51347    267978
AFLR3 GG : Nodes, Elements   =     51347    279503
AFLR3 GG : Nodes, Elements   =     51347    276655
AFLR3 GG : Nodes, Elements   =     54102    284933
AFLR3 GG : Nodes, Elements   =     54102    295744
AFLR3 GG : Nodes, Elements   =     54102    293001
AFLR3 GG : Nodes, Elements   =     56673    300728
AFLR3 GG : Nodes, Elements   =     56673    310793
AFLR3 GG : Nodes, Elements   =     56673    308290
AFLR3 GG : Nodes, Elements   =     59079    315519
AFLR3 GG : Nodes, Elements   =     59079    324941
AFLR3 GG : Nodes, Elements   =     59079    322626
AFLR3 GG : Nodes, Elements   =     61382    329543
AFLR3 GG : Nodes, Elements   =     61382    338630
AFLR3 GG : Nodes, Elements   =     61382    336341
AFLR3 GG : Nodes, Elements   =     63490    342673
AFLR3 GG : Nodes, Elements   =     63490    350891
AFLR3 GG : Nodes, Elements   =     63490    348892
AFLR3 GG : Nodes, Elements   =     65447    354767
AFLR3 GG : Nodes, Elements   =     65447    362598
AFLR3 GG : Nodes, Elements   =     65447    360665
AFLR3 GG : Nodes, Elements   =     67275    366158
AFLR3 GG : Nodes, Elements   =     67275    373226
AFLR3 GG : Nodes, Elements   =     67275    371459
AFLR3 GG : Nodes, Elements   =     68996    376624
AFLR3 GG : Nodes, Elements   =     68996    383423
AFLR3 GG : Nodes, Elements   =     68996    381772
AFLR3 GG : Nodes, Elements   =     70630    386680
AFLR3 GG : Nodes, Elements   =     70630    393034
AFLR3 GG : Nodes, Elements   =     70630    391446
AFLR3 GG : Nodes, Elements   =     72120    395919
AFLR3 GG : Nodes, Elements   =     72120    401703
AFLR3 GG : Nodes, Elements   =     72120    400336
AFLR3 GG : Nodes, Elements   =     73553    404642
AFLR3 GG : Nodes, Elements   =     73553    410203
AFLR3 GG : Nodes, Elements   =     73553    408815
AFLR3 GG : Nodes, Elements   =     74838    412672
AFLR3 GG : Nodes, Elements   =     74838    417713
AFLR3 GG : Nodes, Elements   =     74838    416500
AFLR3 GG : Nodes, Elements   =     76032    420082
AFLR3 GG : Nodes, Elements   =     76032    424744
AFLR3 GG : Nodes, Elements   =     76032    423595
AFLR3 GG : Nodes, Elements   =     77138    426913
AFLR3 GG : Nodes, Elements   =     77138    431199
AFLR3 GG : Nodes, Elements   =     77138    430189
AFLR3 GG : Nodes, Elements   =     78109    433103
AFLR3 GG : Nodes, Elements   =     78109    436892
AFLR3 GG : Nodes, Elements   =     78109    435963
AFLR3 GG : Nodes, Elements   =     78981    438582
AFLR3 GG : Nodes, Elements   =     78981    442022
AFLR3 GG : Nodes, Elements   =     78981    441130
AFLR3 GG : Nodes, Elements   =     79665    443183
AFLR3 GG : Nodes, Elements   =     79665    445915
AFLR3 GG : Nodes, Elements   =     79665    445213
AFLR3 GG : Nodes, Elements   =     80196    446807
AFLR3 GG : Nodes, Elements   =     80196    448977
AFLR3 GG : Nodes, Elements   =     80196    448380
AFLR3 GG : Nodes, Elements   =     80589    449560
AFLR3 GG : Nodes, Elements   =     80589    451169
AFLR3 GG : Nodes, Elements   =     80589    450698
AFLR3 GG : Nodes, Elements   =     80839    451448
AFLR3 GG : Nodes, Elements   =     80839    452521
AFLR3 GG : Nodes, Elements   =     80839    452168
AFLR3 GG : Nodes, Elements   =     80992    452627
AFLR3 GG : Nodes, Elements   =     80992    453306
AFLR3 GG : Nodes, Elements   =     80992    453075
AFLR3 GG : Nodes, Elements   =     81061    453282
AFLR3 GG : Nodes, Elements   =     81061    453581
AFLR3 GG : Nodes, Elements   =     81061    453479
AFLR3 GG : Nodes, Elements   =     81085    453551
AFLR3 GG : Nodes, Elements   =     81085    453664
AFLR3 GG : Nodes, Elements   =     81085    453610
AFLR3 GG : Nodes, Elements   =     81092    453631
AFLR3 GG : Nodes, Elements   =     81092    453658
AFLR3 GG : Nodes, Elements   =     81092    453652
AFLR3 GG : Nodes, Elements   =     81095    453661
AFLR3 GG : Nodes, Elements   =     81095    453676
AFLR3 GG : Nodes, Elements   =     81095    453669
AFLR3 GG : Nodes, Elements   =     81097    453675
AFLR3 GG : Nodes, Elements   =     81097    453684
AFLR3 GG : Nodes, Elements   =     81097    453679
AFLR3 GG : Nodes, Elements   =     81107    453709
AFLR3 GG : Nodes, Elements   =     81107    453743
AFLR3 GG : Nodes, Elements   =     81107    453730
 
AFLR3    : CPU Time          =     4.607   seconds
 
AFLR3 QI : QUALITY IMPROVEMENT
 
AFLR3 QI : Nodes, Elements   =     81107    453730
AFLR3 QI : Nodes, Elements   =     80688    451394
AFLR3 QI : Nodes, Elements   =     80647    451162
AFLR3 QI : Nodes, Elements   =     80641    451126
AFLR3 QI : Nodes, Elements   =     80637    451104
AFLR3 QI : Nodes, Elements   =     80636    451098
AFLR3 QI : Nodes, Elements   =     80635    451093
AFLR3 QI : Nodes, Elements   =     80635    453060
AFLR3 QI : Nodes, Elements   =     80635    450958
AFLR3 QI : Nodes, Elements   =     80635    450051
AFLR3 QI : Nodes, Elements   =     80635    450305
AFLR3 QI : Nodes, Elements   =     80635    449894
AFLR3 QI : Nodes, Elements   =     80635    449759
 
AFLR3    : CPU Time          =     1.184   seconds
 
AFLR3    : DONE

UG3      : DIHEDRAL ANGLE CHECK

UG3      : No. Tet Elems     =    449759
UG3      : Min, Max Ang      =     11.08       159
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     =    449759
UG3      : Min Vol           =  8.97e-07
UG3      : Average Vol       =      8.27
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     =    449759
UG3      : Min, Max Q        =     0.194         1
UG3      : Average Q         =     0.896
UG3      : No. Q<       0.1  =         0
UG3      : No. Q<      0.01  =         0
Volume mesh:
	Number of nodes = 80635
	Number of elements = 468421
	Number of triangles = 18662
	Number of quadrilatarals = 0
	Number of tetrahedrals = 449759
	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
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
 su2AIM/aimDiscr: Found link for attrMap (Attribute_Map) from parent
 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.
80635 points.
2 surface markers.
+------------------------------------+
| Index|        Marker|      Elements|
+------------------------------------+
|     0|             1|         18026|
|     1|             2|           636|
+------------------------------------+
449759 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|     80635|    1/1.00|        10|
|         1|     13339|    1/6.05|      8.23|
|         2|      2076|    1/6.43|      6.64|
+-------------------------------------------+
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: 2.72364e-05. Max. DT: 0.133397. CFL: 10.
MG level: 1 -> Min. DT: 9.1935e-05. Max. DT: 0.178602. CFL: 8.23426.
MG level: 2 -> Min. DT: 7.71048e-05. Max. DT: 0.255542. CFL: 6.64381.
-------------------------------------------------------------------------

----------------------- 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   7.462604    -1.763371      3.705735      -0.192371       0.436795
    1   7.353016    -1.702701      3.773519       0.028637       0.244155
    2   7.406936    -1.722466      3.752912       0.163415       0.077610
    3   7.299623    -1.844952      3.628954       0.202665       0.021678

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

    4   7.250985    -1.878316      3.591308       0.207843       0.012431

----------------------------- 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=6.266591e+09, tgt=6.266591e+09, diff=4.747200e-02
Bound lowerWing: Normalized Integrated Pressure
  Rank=0: src=6.103236e+09, tgt=6.103236e+09, diff=1.198493e+01
Bound leftTip: Normalized Integrated Pressure
  Rank=0: src=6.123436e+07, tgt=6.123436e+07, diff=7.450581e-08
Bound riteTip: Normalized Integrated Pressure
  Rank=0: src=6.123699e+07, tgt=6.123699e+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.
80635 points.
2 surface markers.
+------------------------------------+
| Index|        Marker|      Elements|
+------------------------------------+
|     0|             1|         18026|
|     1|             2|           636|
+------------------------------------+
449759 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: 8.96761e-07, max. volume: 4604.53.
Min. distance: 0.00782053, max. distance: 132.146.

# ILU preconditioner.

# FGMRES residual history
# Residual tolerance target = 1e-14
# Initial residual norm     = 8.35149
     0     1
     10     0.00159481
     20     4.42088e-05
     30     7.00016e-06
     40     9.1219e-07
     50     1.07187e-07
     60     5.97433e-09
     70     3.08946e-10
     80     1.40899e-11
     90     7.47157e-13
     100     4.58423e-14
     110     3.45125e-14
     120     3.44984e-14
     130     3.44984e-14
     140     3.44984e-14
     150     3.44984e-14
     160     3.44984e-14
     170     3.44921e-14
     180     2.57566e-14
# FGMRES final (true) residual:
# Iteration = 184: |res|/|res0| = 8.80866e-15.

Computing volumes of the grid elements.
Non-linear iter.: 1/3. Linear iter.: 184. Min. volume: 0.435364. Error: 7.35655e-14.
Computing volumes of the grid elements.
Min. volume: 0.435364, max. volume: 2.28087e+10.
Min. distance: 8.2037, max. distance: 12612.7.

# ILU preconditioner.

# FGMRES residual history
# Residual tolerance target = 1e-14
# Initial residual norm     = 9825.49
     0     1
     10     0.0453933
     20     0.0424176
     30     0.0380687
     40     0.0289779
     50     0.0199878
     60     0.0182785
     70     0.0125031
     80     0.0117966
     90     0.0114034
     100     0.0110098
     110     0.0104683
     120     0.00966773
     130     0.00863339
     140     0.00781704
     150     0.00712717
     160     0.00650164
     170     0.00563683
     180     0.00505568
     190     0.00443229
     200     0.00383472
     210     0.00347388
     220     0.00335185
     230     0.0032493
     240     0.00304508
     250     0.00259539
     260     0.00231572
     270     0.00206919
     280     0.00187345
     290     0.0017442
     300     0.00161658
     310     0.00144229
     320     0.00126515
     330     0.00115311
     340     0.00108805
     350     0.00102692
     360     0.000994636
     370     0.000944419
     380     0.00090963
     390     0.000858487
     400     0.000822332
     410     0.000792539
     420     0.000763822
     430     0.000736001
     440     0.000717329
     450     0.000704998
     460     0.00069235
     470     0.000679604
     480     0.000666487
     490     0.000648829
     500     0.000625826
# FGMRES final (true) residual:
# Iteration = 500: |res|/|res0| = 0.000625826.

# WARNING in CSysSolve::FGMRES_LinSolver(): 
# true residual norm and calculated residual norm do not agree.
# res = 6.14905, beta = 6.14905, tol = 1e-13.
# res - beta = -1.31995e-08

Computing volumes of the grid elements.
Non-linear iter.: 2/3. Linear iter.: 500. Min. volume: 2.04751. Error: 6.14905.
Computing volumes of the grid elements.
Min. volume: 2.04751, max. volume: 3.17711e+12.
Min. distance: 8.69562, max. distance: 83921.

# ILU preconditioner.

# FGMRES residual history
# Residual tolerance target = 1e-14
# Initial residual norm     = 46465.7
     0     1
     10     0.0123393
     20     0.00818819
     30     0.00629744
     40     0.00537934
     50     0.00483326
     60     0.00427599
     70     0.00344738
     80     0.00301137
     90     0.00274502
     100     0.00259851
     110     0.00234253
     120     0.00195934
     130     0.00172567
     140     0.00159486
     150     0.00146313
     160     0.00137215
     170     0.0013296
     180     0.00127507
     190     0.00115739
     200     0.00102302
     210     0.000929906
     220     0.000836904
     230     0.000789694
     240     0.000750187
     250     0.000735319
     260     0.000700804
     270     0.000619463
     280     0.000527188
     290     0.00050172
     300     0.000464255
     310     0.00043098
     320     0.000389602
     330     0.000371905
     340     0.000360685
     350     0.000349863
     360     0.000331935
     370     0.000321595
     380     0.000310673
     390     0.000291505
     400     0.000276267
     410     0.000267133
     420     0.000250186
     430     0.000237736
     440     0.000227828
     450     0.000215164
     460     0.000203287
     470     0.000192251
     480     0.000184688
     490     0.000176843
     500     0.000167501
# FGMRES final (true) residual:
# Iteration = 500: |res|/|res0| = 0.000167501.

# WARNING in CSysSolve::FGMRES_LinSolver(): 
# true residual norm and calculated residual norm do not agree.
# res = 7.78306, beta = 7.78306, tol = 1e-13.
# res - beta = 4.70024e-11

Computing volumes of the grid elements.
Non-linear iter.: 3/3. Linear iter.: 500. Min. volume: 7.86805. Error: 7.78306.

----------------------- 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 216.007619 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.
80635 points.
2 surface markers.
+------------------------------------+
| Index|        Marker|      Elements|
+------------------------------------+
|     0|             1|         18026|
|     1|             2|           636|
+------------------------------------+
449759 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: 3.16e+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: 2.58. Mean K: 0.00749. Standard deviation K: 0.0495.
Checking for periodicity.
Setting the multigrid structure.
+-------------------------------------------+
|  MG Level|       CVs|Aggl. Rate|       CFL|
+-------------------------------------------+
|         0|     80635|    1/1.00|        10|
|         1|     13327|    1/6.05|      8.23|
|         2|      2043|    1/6.52|      6.61|
+-------------------------------------------+
Semi-span length = 3.22e+04 m.
Wetted area = 1.97e+10 m^2.
Area projection in the x-plane = 8.36e+09 m^2, y-plane = 6.11e+09 m^2, z-plane = 5.77e+08 m^2.
Max. coordinate in the x-direction = 1.37e+03 m, y-direction = 3.22e+04 m, z-direction = 0.169 m.
Min coordinate in the x-direction = -1.52e+04 m, y-direction = -3.13e+04 m, z-direction = -3.52e+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: 0.00112936. Max. DT: 424.101. CFL: 10.
MG level: 1 -> Min. DT: 0.0815049. Max. DT: 632.91. CFL: 8.23179.
MG level: 2 -> Min. DT: 0.155331. Max. DT: 770.942. CFL: 6.60842.
-------------------------------------------------------------------------

----------------------- Residual Evolution Summary ----------------------
log10[Maximum residual]: 12.429.
Maximum residual point 28555, located at (213662, -62818.8, -237687).
There are 6771 non-physical points in the solution.
-------------------------------------------------------------------------

 Iter    Time(s)     Res[Rho]     Res[RhoE]      CL(Total)      CD(Total)
    0   6.257764    10.335562     15.804667  -10000.000000   10000.000000
    1   6.374335    10.854566     16.407863  -10000.000000   10000.000000
    2   6.387372    11.128353     16.896326  -10000.000000   10000.000000
    3   6.404972    11.437769     17.190290  -10000.000000   10000.000000

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

    4   6.409964    11.742587     17.327818  -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 22490 non-physical points in the solution.
Warning: 2454 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=1.258889e+10, tgt=1.258887e+10, diff=1.847812e+04
Bound lowerWing: Normalized Integrated Pressure
  Rank=0: src=9.833916e+09, tgt=9.833916e+09, diff=3.155332e+02
Bound leftTip: Normalized Integrated Pressure
  Rank=0: src=8.817431e+07, tgt=8.817431e+07, diff=0.000000e+00
Bound riteTip: Normalized Integrated Pressure
  Rank=0: src=1.417603e+08, tgt=1.417603e+08, diff=1.276550e-02

==> 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	6m54.485s
user	7m28.300s
sys	2m23.200s
+ status=0
+ set +x

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


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


All tests pass!

[Execution node] check if [reynolds] 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: '/jenkins/workspace/ESP_QuickTestCaps/7.4/CAPS/training/LINUX64')
[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: '/jenkins/workspace/ESP_QuickTestCaps/7.4/CAPS/training/LINUX64')
[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,LINUX64,reynolds)
[Static Analysis] Using reference build 'ESP_QuickTestCaps/CASREV=7.4,ESP_ARCH=LINUX64,buildnode=reynolds #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=LINUX64,buildnode=reynolds #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