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
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