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Full Logexecuting [ 85] ifthen: 0.00000 EQ 1.00000 and ... executing [ 88] ifthen: 1.00000 NE 0.00000 OR ... executing [ 89] set: makeWingOml 1 makeWingOml = 1.00000 0.00000 executing [ 90] set: makeWingWaffle 1 makeWingWaffle = 1.00000 0.00000 executing [ 92] ifthen: 0.00000 EQ 1.00000 and ... executing [ 95] ifthen: 0.00000 NE 0.00000 and ... executing [ 101] ifthen: 1.00000 EQ 1.00000 and 0.00000 eq 0.00000 executing [ 102] set: COMP:Fuse 0 COMP:Fuse = 0.00000 0.00000 executing [ 104] ifthen: 0.00000 EQ 1.00000 and ... executing [ 107] ifthen: 1.00000 EQ 1.00000 and 0.00000 eq 0.00000 executing [ 108] set: COMP:Htail 0 COMP:Htail = 0.00000 0.00000 executing [ 110] ifthen: 1.00000 EQ 1.00000 and 0.00000 eq 0.00000 executing [ 111] set: COMP:Vtail 0 COMP:Vtail = 0.00000 0.00000 executing [ 113] ifthen: 1.00000 EQ 1.00000 and 0.00000 eq 0.00000 executing [ 114] set: COMP:Pylon 0 COMP:Pylon = 0.00000 0.00000 executing [ 116] ifthen: 1.00000 EQ 1.00000 and 0.00000 eq 0.00000 executing [ 117] set: COMP:Pod 0 COMP:Pod = 0.00000 0.00000 executing [ 119] ifthen: 1.00000 EQ 1.00000 and 0.00000 eq 0.00000 executing [ 120] set: COMP:Control 0 COMP:Control = 0.00000 0.00000 executing [ 122] ifthen: 0.00000 EQ 0.00000 and 0.00000 eq 0.00000 executing [ 123] set: makeFuseOml 0 makeFuseOml = 0.00000 0.00000 executing [ 124] set: makeFuseWaffle 0 makeFuseWaffle = 0.00000 0.00000 executing [ 125] set: makeFuseCmass 0 makeFuseCmass = 0.00000 0.00000 executing [ 127] ifthen: 1.00000 EQ 0.00000 and ... executing [ 133] ifthen: 0.00000 EQ 0.00000 and 0.00000 eq 0.00000 executing [ 134] set: makeHtailOml 0 makeHtailOml = 0.00000 0.00000 executing [ 135] set: makeHtailHinge 0 makeHtailHinge = 0.00000 0.00000 executing [ 136] set: makeHtailWaffle 0 makeHtailWaffle = 0.00000 0.00000 executing [ 137] set: makeHtailCmass 0 makeHtailCmass = 0.00000 0.00000 executing [ 139] ifthen: 0.00000 EQ 0.00000 and 0.00000 eq 0.00000 executing [ 140] set: makeVtailOml 0 makeVtailOml = 0.00000 0.00000 executing [ 141] set: makeVtailHinge 0 makeVtailHinge = 0.00000 0.00000 executing [ 142] set: makeVtailWaffle 0 makeVtailWaffle = 0.00000 0.00000 executing [ 143] set: makeVtailCmass 0 makeVtailCmass = 0.00000 0.00000 executing [ 145] ifthen: 0.00000 EQ 0.00000 and 0.00000 eq 0.00000 executing [ 146] set: makePylonOml 0 makePylonOml = 0.00000 0.00000 executing [ 148] ifthen: 0.00000 EQ 0.00000 and 0.00000 eq 0.00000 executing [ 149] set: makePodOml 0 makePodOml = 0.00000 0.00000 executing [ 151] ifthen: 0.00000 EQ 0.00000 and 0.00000 eq 0.00000 executing [ 152] set: makeWingHinge 0 makeWingHinge = 0.00000 0.00000 executing [ 153] set: makeHtailHinge 0 makeHtailHinge = 0.00000 0.00000 executing [ 154] set: makeVtailHinge 0 makeVtailHinge = 0.00000 0.00000 executing [ 156] end: executing [ 157] set: wing:span sqrt(wing:aspect*wing:area) wing:span = 7.74597 0.00000 executing [ 158] set: wing:chordr 2*wing:area/wing:span/(1+wing:taper) wing:chordr = 1.61374 0.00000 executing [ 159] set: wing:chordt wing:chordr*wing:taper wing:chordt = 0.96825 0.00000 executing [ 160] set: wing:ytip -wing:span/2 wing:ytip = -3.87298 0.00000 executing [ 161] set: wing:xtip -wing:ytip*tand(wing:sweep) wing:xtip = 1.40965 0.00000 executing [ 162] set: wing:ztip -wing:ytip*tand(wing:dihedral) wing:ztip = 0.27083 0.00000 executing [ 163] set: wing:mac sqrt(wing:area/wing:aspect) wing:mac = 1.29099 0.00000 executing [ 164] ifthen: 1.00000 EQ 1.00000 and 0.00000 eq 0.00000 executing [ 165] mark: Mark created executing [ 166] udprim: naca thickness 0.12000 camber 0.06000 sharpte 0.00000 (compiled code) Body 1 created (toler= 1.0000e-07, nnode= 3, nedge= 3, nface= 1) executing [ 167] scale: 1.61374 0.00000 0.00000 0.00000 Body 2 created (toler= 1.6137e-07, nnode= 3, nedge= 3, nface= 1) executing [ 168] rotatex: 90.00000 0.00000 0.00000 Body 3 created (toler= 1.6137e-07, nnode= 3, nedge= 3, nface= 1) executing [ 169] udprim: naca thickness 0.16000 camber 0.02000 sharpte 0.00000 (compiled code) Body 4 created (toler= 1.0000e-07, nnode= 3, nedge= 3, nface= 1) executing [ 170] scale: 0.96825 0.00000 0.00000 0.00000 Body 5 created (toler= 1.0000e-07, nnode= 3, nedge= 3, nface= 1) executing [ 171] rotatex: 90.00000 0.00000 0.00000 Body 6 created (toler= 1.0000e-07, nnode= 3, nedge= 3, nface= 1) executing [ 172] rotatey: -5.00000 0.00000 0.00000 Body 7 created (toler= 1.0000e-07, nnode= 3, nedge= 3, nface= 1) executing [ 173] translate: 1.40965 -3.87298 0.27083 Body 8 created (toler= 1.0000e-07, nnode= 3, nedge= 3, nface= 1) executing [ 174] rule: 0.00000 0.00000 ruling 2 Xsects with 3 Strips each... Body 9 created (toler= 1.0000e-07, nnode= 6, nedge= 9, nface= 5) executing [ 175] set: ruledBody @nbody ruledBody = 9.00000 0.00000 executing [ 176] select: face 9 1 putting Branch Attributes on Face 4 executing [ 177] select: face 9 2 putting Branch Attributes on Face 5 executing [ 178] select: face 9 3 putting Branch Attributes on Face 1 executing [ 179] select: face 9 4 putting Branch Attributes on Face 2 executing [ 180] select: edge 9 3 9 4 1 putting Branch Attributes on Edge 3 executing [ 181] ifthen: 0.00000 EQ 0.00000 and 0.00000 eq 0.00000 executing [ 182] select: face 9 5 putting Branch Attributes on Face 3 executing [ 186] store: LeftWing 0.00000 1.00000 Body 9 stored executing [ 187] restore: LeftWing 0.00000 Body 10 restored (toler= 1.0000e-07, nnode= 6, nedge= 9, nface= 5) executing [ 188] select: face tagType tip * * * * putting Branch Attributes on Face 5 executing [ 189] select: edge tagType leadingEdge * * * * executing [ 190] ifthen: 3.00000 GT 0.00000 and 0.00000 eq 0.00000 executing [ 191] select: edge tagType leadingEdge * * * * putting Branch Attributes on Edge 3 executing [ 193] select: edge tagType trailingEdge * * * * ERROR:: (edge_not_found) in Branch Brch_000193 at [[../ESP/wing3.csm:103]] SELECT specified nonexistant Edge executing [ 197] catbeg: $edge_not_found --> catching signal -223 (edge_not_found) executing [ 199] mirror: 0.00000 1.00000 0.00000 0.00000 Body 11 created (toler= 1.0000e-07, nnode= 6, nedge= 9, nface= 5) executing [ 200] join: 0.00000 0.00000 Body 12 created (toler= 1.0000e-07, nnode= 9, nedge= 15, nface= 8) executing [ 201] select: edge 9 3 9 3 1 putting Branch Attributes on Edge 2 executing [ 202] select: edge 9 4 9 4 1 putting Branch Attributes on Edge 5 executing [ 203] store: WingOml 0.00000 0.00000 Body 12 stored executing [ 205] ifthen: 1.00000 EQ 1.00000 and 0.00000 eq 0.00000 executing [ 206] restore: WingOml 0.00000 Body 13 restored (toler= 1.0000e-07, nnode= 9, nedge= 15, nface= 8) executing [ 207] set: xmin @xmin-0.1 xmin = -0.10102 0.00000 executing [ 208] set: xmax @xmax+0.1 xmax = 2.47425 0.00000 executing [ 209] set: ymin 0 ymin = 0.00000 0.00000 executing [ 210] set: ymax @ymax+0.1 ymax = 3.97298 0.00000 executing [ 211] set: zmin @zmin-0.1 zmin = -0.13316 0.00000 executing [ 212] set: zmax @zmax+0.1 zmax = 0.49998 0.00000 executing [ 213] store: . 0.00000 0.00000 Body 13 removed from stack executing [ 214] udparg: waffle depth 3.00000 Body 14 created (NULL Body) executing [ 215] udparg: waffle depth 0.20000 Body 15 created (NULL Body) executing [ 216] udparg: waffle depth 0.70000 Body 16 created (NULL Body) executing [ 217] udprim: waffle depth 0.63315 filename tmp_OpenCSM_00/00 (compiled code) processing: processing: # construction lines for spars processing: CPOINT A AT 0+wing:spar1*wing:chordr 0 processing: CPOINT B AT wing:xtip+wing:spar1*wing:chordt -wing:ytip processing: CPOINT C AT 0+wing:spar2*wing:chordr 0 processing: CPOINT D AT wing:xtip+wing:spar2*wing:chordt -wing:ytip processing: processing: CLINE AB A B processing: CLINE CD C D processing: processing: # rite spars processing: POINT E ON AB YLOC ymin processing: POINT F ON AB YLOC ymax processing: LINE EF E F tagComp=riteWing tagType=spar tagIndex=1 processing: processing: POINT G ON CD YLOC ymin processing: POINT H ON CD YLOC ymax processing: LINE GH G H tagComp=riteWing tagType=spar tagIndex=2 processing: processing: # rite ribs processing: PATBEG irib wing:nrib processing: CPOINT I AT xmin -wing:ytip*irib/(wing:nrib+1) processing: CPOINT J AT xmax y@I processing: LINE . I J tagComp=riteWing tagType=rib tagIndex=!val2str(irib,0) processing: PATEND processing: CPOINT I AT xmin -wing:ytip*irib/(wing:nrib+1) processing: CPOINT J AT xmax y@I processing: LINE . I J tagComp=riteWing tagType=rib tagIndex=!val2str(irib,0) processing: PATEND processing: CPOINT I AT xmin -wing:ytip*irib/(wing:nrib+1) processing: CPOINT J AT xmax y@I processing: LINE . I J tagComp=riteWing tagType=rib tagIndex=!val2str(irib,0) processing: PATEND processing: processing: # root rib processing: CPOINT I AT xmin 0 processing: CPOINT J AT xmax y@I processing: LINE . I J tagComp=rootWing tagType=rib tagIndex=0 processing: processing: # left spars processing: POINT E AT x@E -y@E processing: POINT F AT x@F -y@F processing: LINE FE F E tagComp=leftWing tagType=spar tagIndex=1 processing: processing: POINT G AT x@G -y@G processing: POINT H AT x@H -y@H processing: LINE HG H G tagComp=leftWing tagType=spar tagIndex=2 processing: processing: # left ribs processing: PATBEG irib wing:nrib processing: CPOINT I AT xmin wing:ytip*irib/(wing:nrib+1) processing: CPOINT J AT xmax y@I processing: LINE . I J tagComp=leftWing tagType=rib tagIndex=!val2str(irib,0) processing: PATEND processing: CPOINT I AT xmin wing:ytip*irib/(wing:nrib+1) processing: CPOINT J AT xmax y@I processing: LINE . I J tagComp=leftWing tagType=rib tagIndex=!val2str(irib,0) processing: PATEND processing: CPOINT I AT xmin wing:ytip*irib/(wing:nrib+1) processing: CPOINT J AT xmax y@I processing: LINE . I J tagComp=leftWing tagType=rib tagIndex=!val2str(irib,0) processing: PATEND Body 17 created (toler= 1.0000e-07, nnode= 64, nedge= 106, nface= 37) executing [ 218] translate: 0.00000 0.00000 -0.13316 Body 18 created (toler= 1.0000e-07, nnode= 64, nedge= 106, nface= 37) executing [ 219] store: WingWaffle 0.00000 0.00000 Body 18 stored executing [ 221] udprim: $/capsViews (scripted code) [ 222] interface: . ALL 0.00000 executing [ 223] ifthen: 0.00000 NE 0.00000 and ... executing [ 268] ifthen: 1.00000 NE 0.00000 and 0.00000 eq 0.00000 executing [ 269] udprim: $/viewVLM (scripted code) [ 270] interface: . ALL 0.00000 executing [ 271] set: vlmAIMs $avlAIM;$astrosAIM;nastranAIM;egadsTessAIM vlmAIMs = $avlAIM;$astrosAIM;nastranAIM;egadsTessAIM executing [ 272] ifthen: 1.00000 EQ 1.00000 and 0.00000 eq 0.00000 executing [ 273] restore: WingOml 0.00000 Body 19 restored (toler= 1.0000e-07, nnode= 9, nedge= 15, nface= 8) executing [ 274] set: xmin @xmin-1 xmin = -1.00102 0.00000 executing [ 275] set: xmax @xmax+1 xmax = 3.37425 0.00000 executing [ 276] set: ymin @ymin+0.001 ymin = -3.87198 0.00000 executing [ 277] set: ymax @ymax-0.001 ymax = 3.87198 0.00000 executing [ 278] set: zmin @zmin-1 zmin = -1.03316 0.00000 executing [ 279] set: zmax @zmax+1 zmax = 1.39998 0.00000 executing [ 280] store: . 0.00000 0.00000 Body 19 removed from stack executing [ 281] set: WingVlmNcut 3 WingVlmNcut = 3.00000 0.00000 executing [ 282] mark: Mark created executing [ 283] patbeg: icut 3.00000 pattern counter: icut = 1 executing [ 284] set: y ymin+(ymax-ymin)*(icut-1)/(WingVlmNcut-1) y = -3.87198 0.00000 executing [ 285] box: -1.00102 -3.87198 -1.03316 4.37527 0.00000 2.43315 Body 20 created (toler= 1.0000e-07, nnode= 4, nedge= 4, nface= 1) executing [ 286] restore: WingOml 0.00000 Body 21 restored (toler= 1.0000e-07, nnode= 9, nedge= 15, nface= 8) executing [ 287] intersect: none 1.00000 0.0000e+00 Body 22 created (toler= 5.0000e-06, nnode= 3, nedge= 3, nface= 1) executing [ 288] select: face 1 putting Branch Attributes on Face 1 executing [ 289] patend: pattern counter: icut = 2 executing [ 284] set: y ymin+(ymax-ymin)*(icut-1)/(WingVlmNcut-1) y = 0.00000 0.00000 executing [ 285] box: -1.00102 0.00000 -1.03316 4.37527 0.00000 2.43315 Body 23 created (toler= 1.0000e-07, nnode= 4, nedge= 4, nface= 1) executing [ 286] restore: WingOml 0.00000 Body 24 restored (toler= 1.0000e-07, nnode= 9, nedge= 15, nface= 8) executing [ 287] intersect: none 1.00000 0.0000e+00 Body 25 created (toler= 1.0000e-07, nnode= 3, nedge= 3, nface= 1) executing [ 288] select: face 1 putting Branch Attributes on Face 1 executing [ 289] patend: pattern counter: icut = 3 executing [ 284] set: y ymin+(ymax-ymin)*(icut-1)/(WingVlmNcut-1) y = 3.87198 0.00000 executing [ 285] box: -1.00102 3.87198 -1.03316 4.37527 0.00000 2.43315 Body 26 created (toler= 1.0000e-07, nnode= 4, nedge= 4, nface= 1) executing [ 286] restore: WingOml 0.00000 Body 27 restored (toler= 1.0000e-07, nnode= 9, nedge= 15, nface= 8) executing [ 287] intersect: none 1.00000 0.0000e+00 Body 28 created (toler= 5.0000e-06, nnode= 3, nedge= 3, nface= 1) executing [ 288] select: face 1 putting Branch Attributes on Face 1 executing [ 289] patend: executing [ 290] ifthen: 1.00000 EQ 0.00000 and ... executing [ 299] ifthen: 0.00000 EQ 1.00000 and ... executing [ 321] group: 0.00000 Body 25 added to Group 28 Body 22 added to Group 28 executing [ 323] ifthen: 0.00000 EQ 1.00000 and ... executing [ 365] ifthen: 0.00000 EQ 1.00000 and ... executing [ 407] end: executing [ 409] ifthen: 0.00000 NE 0.00000 and ... executing [ 852] ifthen: 0.00000 NE 0.00000 and ... executing [1290] ifthen: 1.00000 NE 0.00000 OR ... executing [1291] udprim: $/viewStructure (scripted code) [1292] interface: . ALL 0.00000 executing [1293] set: structAIMs $nastranAIM;astrosAIM;mystranAIM;egadsTessAIM structAIMs = $nastranAIM;astrosAIM;mystranAIM;egadsTessAIM executing [1294] ifthen: 1.00000 EQ 1.00000 and 0.00000 eq 0.00000 executing [1295] restore: WingOml 0.00000 Body 29 restored (toler= 1.0000e-07, nnode= 9, nedge= 15, nface= 8) executing [1296] restore: WingWaffle 0.00000 Body 30 restored (toler= 1.0000e-07, nnode= 64, nedge= 106, nface= 37) executing [1297] intersect: none 1.00000 0.0000e+00 Body 31 created (toler= 5.0000e-06, nnode= 57, nedge= 99, nface= 37) executing [1298] restore: WingOml 0.00000 Body 32 restored (toler= 1.0000e-07, nnode= 9, nedge= 15, nface= 8) executing [1299] restore: WingWaffle 0.00000 Body 33 restored (toler= 1.0000e-07, nnode= 64, nedge= 106, nface= 37) executing [1300] subtract: none 1.00000 0.0000e+00 Body 34 created (toler= 6.7429e-07, nnode= 63, nedge= 123, nface= 62) executing [1301] extract: 0 Body 35 created (toler= 6.7429e-07, nnode= 63, nedge= 123, nface= 62) executing [1302] union: 0.00000 0 0.0000e+00 Body 36 created (toler= 5.0000e-06, nnode= 63, nedge= 137, nface= 99) executing [1303] ifthen: 0.00000 EQ 1.00000 and ... executing [1306] else: executing [1307] udprim: editAttr filename tmp_OpenCSM_00/05 (compiled code) processing: FACE HAS tagComp=leftWing processing: SET capsGroup=leftWingSkin processing: processing: FACE HAS tagComp=riteWing processing: SET capsGroup=riteWingSkin processing: processing: FACE HAS tagType=tip processing: SET capsGroup=wingRib processing: processing: FACE HAS tagType=trailingEdge processing: SET capsGroup=wingTE processing: processing: FACE HAS tagType=rib processing: SET capsGroup=wingRib processing: processing: FACE HAS tagType=spar tagIndex=1 processing: SET capsGroup=wingSpar1 processing: SET capsMesh=wingSpar1 processing: processing: FACE HAS tagType=spar tagIndex=2 processing: SET capsGroup=wingSpar2 processing: SET capsMesh=wingSpar2 WARNING:: toler = 5.0000e-06 for UDPRIM Body 37 created (toler= 5.0000e-06, nnode= 63, nedge= 137, nface= 99) executing [1309] udprim: editAttr filename tmp_OpenCSM_00/06 (compiled code) processing: FACE HAS tagType=upper processing: SET capsBound=upperWing processing: processing: FACE HAS tagType=lower processing: SET capsBound=lowerWing processing: processing: FACE HAS tagType=tip tagIndex=1 processing: SET capsBound=leftTip processing: processing: FACE HAS tagType=tip tagIndex=2 processing: SET capsBound=riteTip WARNING:: toler = 5.0000e-06 for UDPRIM Body 38 created (toler= 5.0000e-06, nnode= 63, nedge= 137, nface= 99) executing [1310] udprim: editAttr filename tmp_OpenCSM_00/07 (compiled code) processing: NODE ADJ2FACE tagComp=leftWing tagType=tip processing: AND ADJ2FACE tagType=lower processing: AND ADJ2FACE tagType=spar tagIndex=1 processing: SET capsLoad=leftPointLoad processing: processing: NODE ADJ2FACE tagComp=riteWing tagType=tip processing: AND ADJ2FACE tagType=lower processing: AND ADJ2FACE tagType=spar tagIndex=1 processing: SET capsLoad=ritePointLoad WARNING:: toler = 5.0000e-06 for UDPRIM Body 39 created (toler= 5.0000e-06, nnode= 63, nedge= 137, nface= 99) executing [1311] select: edge tagType leadingEdge * * * * executing [1312] dimension: leadingEdges 1.00000 8.00000 executing [1313] set: leadingEdges @sellist leadingEdges[1,1] = 8.00000 0.00000 leadingEdges[1,2] = 31.00000 0.00000 leadingEdges[1,3] = 33.00000 0.00000 leadingEdges[1,4] = 62.00000 0.00000 leadingEdges[1,5] = 64.00000 0.00000 leadingEdges[1,6] = 94.00000 0.00000 leadingEdges[1,7] = 96.00000 0.00000 leadingEdges[1,8] = 121.00000 0.00000 executing [1314] patbeg: i 8.00000 pattern counter: i = 1 executing [1315] select: edge 8 putting Branch Attributes on Edge 8 executing [1316] patend: pattern counter: i = 2 executing [1315] select: edge 31 putting Branch Attributes on Edge 31 executing [1316] patend: pattern counter: i = 3 executing [1315] select: edge 33 putting Branch Attributes on Edge 33 executing [1316] patend: pattern counter: i = 4 executing [1315] select: edge 62 putting Branch Attributes on Edge 62 executing [1316] patend: pattern counter: i = 5 executing [1315] select: edge 64 putting Branch Attributes on Edge 64 executing [1316] patend: pattern counter: i = 6 executing [1315] select: edge 94 putting Branch Attributes on Edge 94 executing [1316] patend: pattern counter: i = 7 executing [1315] select: edge 96 putting Branch Attributes on Edge 96 executing [1316] patend: pattern counter: i = 8 executing [1315] select: edge 121 putting Branch Attributes on Edge 121 executing [1316] patend: executing [1317] udprim: editAttr filename tmp_OpenCSM_00/08 (compiled code) processing: FACE ADJ2EDGE tagComp=leftWing processing: SET tagTemp=leadingEdgeFace WARNING:: toler = 5.0000e-06 for UDPRIM Body 40 created (toler= 5.0000e-06, nnode= 63, nedge= 137, nface= 99) executing [1318] udprim: editAttr filename tmp_OpenCSM_00/09 (compiled code) processing: EDGE ADJ2FACE tagTemp=leadingEdgeFace processing: AND ADJ2FACE tagComp=rootWing processing: SET capsMesh=rootLeadingEdge WARNING:: toler = 5.0000e-06 for UDPRIM Body 41 created (toler= 5.0000e-06, nnode= 63, nedge= 137, nface= 99) executing [1319] ifthen: 1.00000 EQ 1.00000 and 0.00000 eq 0.00000 executing [1320] udprim: editAttr filename tmp_OpenCSM_00/10 (compiled code) processing: FACE HAS tagComp=rootWing processing: SET capsConstraint=rootConstraint processing: processing: EDGE ADJ2FACE tagComp=rootWing processing: SET capsConstraint=rootConstraint processing: processing: NODE ADJ2FACE tagComp=rootWing processing: SET capsConstraint=rootConstraint WARNING:: toler = 5.0000e-06 for UDPRIM Body 42 created (toler= 5.0000e-06, nnode= 63, nedge= 137, nface= 99) executing [1322] ifthen: 0.00000 EQ 1.00000 and ... executing [1325] udprim: editAttr filename tmp_OpenCSM_00/12 (compiled code) processing: FACE HAS tagComp=leftWing tagType=upper processing: AND ADJ2EDGE tagType=leadingEdge processing: AND ADJ2FACE tagComp=riteWing processing: SET tagCsys=leftWing processing: processing: FACE HAS tagComp=riteWing tagType=upper processing: AND ADJ2EDGE tagType=leadingEdge processing: AND ADJ2FACE tagComp=leftWing processing: SET tagCsys=riteWing WARNING:: toler = 5.0000e-06 for UDPRIM Body 43 created (toler= 5.0000e-06, nnode= 63, nedge= 137, nface= 99) executing [1326] select: face tagCsys leftWing * * * * executing [1327] set: leftWingSkinCsys @sellist leftWingSkinCsys = 27.00000 0.00000 executing [1328] select: face tagCsys riteWing * * * * executing [1329] set: riteWingSkinCsys @sellist riteWingSkinCsys = 8.00000 0.00000 executing [1330] store: WingStruct 0.00000 0.00000 Body 43 stored executing [1331] restore: WingStruct 0.00000 Body 44 restored (toler= 5.0000e-06, nnode= 63, nedge= 137, nface= 99) executing [1332] store: WingStruct 0.00000 0.00000 WARNING:: storage WingStruct (0) is being overwritten Body 44 stored executing [1334] restore: WingStruct 0.00000 Body 45 restored (toler= 5.0000e-06, nnode= 63, nedge= 137, nface= 99) executing [1335] select: body putting Branch Attributes on Body executing [1336] ifthen: 0.00000 EQ 1.00000 and ... executing [1339] end: executing [1341] ifthen: 0.00000 NE 0.00000 and ... executing [1378] end: finalizing: ==> Profile information Branch type ncall time (sec) pct dimension 1 0.000 0.0 box 3 0.004 0.0 udprim 14 0.501 1.2 restore 12 0.040 0.1 rule 1 0.079 0.2 intersect 4 4.974 12.1 subtract 1 4.382 10.7 union 1 30.128 73.5 join 1 0.116 0.3 extract 1 0.642 1.6 translate 2 0.021 0.1 rotatex 2 0.003 0.0 rotatey 1 0.001 0.0 scale 2 0.003 0.0 mirror 1 0.023 0.1 interface 4 0.000 0.0 end 4 0.000 0.0 set 77 0.001 0.0 udparg 3 0.000 0.0 select 26 0.058 0.1 store 7 0.000 0.0 patbeg 2 0.000 0.0 patend 11 0.000 0.0 ifthen 48 0.000 0.0 else 2 0.000 0.0 endif 48 0.000 0.0 catbeg 1 0.000 0.0 catend 1 0.000 0.0 mark 2 0.000 0.0 group 1 0.000 0.0 Total 284 40.976 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 7 Name = Wing, index = 1 Name = wingSpar1, index = 2 Name = riteWingSkin, index = 3 Name = wingRib, index = 4 Name = leftWingSkin, index = 5 Name = wingSpar2, index = 6 Name = wingTE, index = 7 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = wingSpar1, index = 1 Name = wingSpar2, index = 2 Name = leadingEdge, index = 3 Name = rootLeadingEdge, index = 4 Getting surface mesh for body 1 (of 4) Tessellating body Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 3 of face 1, unable to assign a boundary index value Number of nodes = 7 Number of elements = 3 Number of node elements = 0 Number of line elements = 0 Number of triangle elements = 0 Number of quadrilateral elements = 3 Getting surface mesh for body 2 (of 4) Tessellating body Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 3 of face 1, unable to assign a boundary index value Number of nodes = 7 Number of elements = 3 Number of node elements = 0 Number of line elements = 0 Number of triangle elements = 0 Number of quadrilateral elements = 3 Getting surface mesh for body 3 (of 4) Tessellating body Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 3 of face 1, unable to assign a boundary index value Number of nodes = 7 Number of elements = 3 Number of node elements = 0 Number of line elements = 0 Number of triangle elements = 0 Number of quadrilateral elements = 3 Getting surface mesh for body 4 (of 4) Tessellating body Number of nodes = 299 Number of elements = 387 Number of node elements = 0 Number of line elements = 0 Number of triangle elements = 0 Number of quadrilateral elements = 387 ---------------------------- Total number of nodes = 320 Total number of elements = 396 Analysis directory does not currently exist - it will be made automatically CAPS Info: No symbol for aimExecute in nastranAIM CAPS Info: No symbol for aimCheck in nastranAIM CAPS Info: No symbol for aimSensitivity in nastranAIM ==> Running Nastran pre-analysis... Mapping Csys attributes ................ Number of unique Csys attributes = 2 Name = leftWingSkin, index = 1 Name = riteWingSkin, index = 2 Getting FEA coordinate systems....... Number of coordinate systems - 2 Coordinate system name - leftWingSkin Coordinate system name - riteWingSkin Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = rootConstraint, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 2 Name = ritePointLoad, index = 1 Name = leftPointLoad, index = 2 Mapping capsBound attributes ................ Number of unique capsBound attributes = 4 Name = lowerWing, index = 1 Name = upperWing, index = 2 Name = riteTip, index = 3 Name = leftTip, index = 4 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Found link for attrMap (Attribute_Map) from parent Found link for a Surface mesh from parent Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 7 Number of elements = 3 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 3 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 7 Number of elements = 3 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 3 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 7 Number of elements = 3 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 3 Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 299 Number of elements = 387 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 387 Combining multiple FEA meshes! Combined Number of nodal coordinates = 320 Combined Number of elements = 396 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 0 Combined Elemental Quad4 = 396 Getting vortex lattice surface data VLM surface name - upperWing Done getting vortex lattice surface data Getting FEA vortex lattice mesh Surface 1: Number of points found for aero-spline = 12 Surface 2: Number of points found for aero-spline = 12 Getting FEA materials....... Number of materials - 2 Material name - Unobtainium No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic" Material name - Madeupium Done getting FEA materials Getting FEA properties....... Number of properties - 5 Property name - leftWingSkin Property name - riteWingSkin Property name - wingRib Property name - wingSpar1 Property name - wingSpar2 Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - rootConstraint No "constraintType" specified for Constraint tuple rootConstraint, defaulting to "ZeroDisplacement" Done getting FEA constraints Support tuple is NULL - No supports applied Connect tuple is NULL - Using defaults Load tuple is NULL - No loads applied Design_Variable tuple is NULL - No design variables applied Design_Constraint tuple is NULL - No design constraints applied Design_Equation tuple is NULL - No design equations applied Design_Table tuple is NULL - No design table constants applied Design_Opt_Param tuple is NULL - No design optimization parameters applied Design_Response tuple is NULL - No design responses applied Design_Equation_Response tuple is NULL - No design equation responses applied Getting FEA analyses....... Number of analyses - 1 Analysis name - Flutter Done getting FEA analyses Writing Nastran grid and connectivity file (in large field format) .... Finished writing Nastran grid file Writing subElement types (if any) - appending mesh file Writing Nastran instruction file.... SUBCASE = 0 Warning: No loads specified for case Flutter!!!! Writing aero card Writing analysis cards Writing constraint ADD cards Writing constraint cards Writing material cards Writing property cards Writing coordinate system cards Writing aeroelastic cards ==> Running Nastran... sh: nastran: command not found --> temporary directory "tmp_OpenCSM_00" removed Cleaning up egadsInstance - 0 Cleaning up nastranInstance - 0 EGADS Info: 906 Objects, 1436 Reference in Use (of 33673) at Close! real 0m13.876s user 0m37.285s sys 0m4.663s + status=0 + set +x ================================================= data/session10/nastran_5_Flutter.py passed (as expected) ================================================= ================================================= aeroelastic_Iterative_SU2_Astros.py test; + python aeroelastic_Iterative_SU2_Astros.py + tee -a /Users/jenkins/workspace/ESP_QuickTestCaps/7.3/CAPS/training/DARWIN64/CAPS/training/training.log Definition of "kt" in "/Users/jenkins/workspace/ESP_QuickTestCaps/7.3/CAPS/training/DARWIN64/ESP/udunits/udunits2-common.xml", line 90, overrides prefixed-unit "1000000 kilogram" Definition of "microns" in "/Users/jenkins/workspace/ESP_QuickTestCaps/7.3/CAPS/training/DARWIN64/ESP/udunits/udunits2-common.xml", line 336, overrides prefixed-unit "1e-15 second" Definition of "ft" in "/Users/jenkins/workspace/ESP_QuickTestCaps/7.3/CAPS/training/DARWIN64/ESP/udunits/udunits2-common.xml", line 433, overrides prefixed-unit "1e-12 kilogram" Definition of "yd" in "/Users/jenkins/workspace/ESP_QuickTestCaps/7.3/CAPS/training/DARWIN64/ESP/udunits/udunits2-common.xml", line 441, overrides prefixed-unit "8.64e-20 second" Definition of "pt" in "/Users/jenkins/workspace/ESP_QuickTestCaps/7.3/CAPS/training/DARWIN64/ESP/udunits/udunits2-common.xml", line 655, overrides prefixed-unit "1e-09 kilogram" Definition of "at" in "/Users/jenkins/workspace/ESP_QuickTestCaps/7.3/CAPS/training/DARWIN64/ESP/udunits/udunits2-common.xml", line 1052, overrides prefixed-unit "1e-15 kilogram" Definition of "ph" in "/Users/jenkins/workspace/ESP_QuickTestCaps/7.3/CAPS/training/DARWIN64/ESP/udunits/udunits2-common.xml", line 1571, overrides prefixed-unit "3.6e-09 second" Definition of "nt" in "/Users/jenkins/workspace/ESP_QuickTestCaps/7.3/CAPS/training/DARWIN64/ESP/udunits/udunits2-common.xml", line 1578, overrides prefixed-unit "1e-06 kilogram" --> enter ocsmCheck() --> checks passed --> enter ocsmSave(filename=capsTmp.cpc) --> enter ocsmCheck() --> checks passed Analysis directory does not currently exist - it will be made automatically CAPS Info: No symbol for aimDiscr in aflr4AIM CAPS Info: No symbol for aimFreeDiscr in aflr4AIM CAPS Info: No symbol for aimLocateElement in aflr4AIM CAPS Info: No symbol for aimUsesDataSet in aflr4AIM CAPS Info: No symbol for aimCheck in aflr4AIM CAPS Info: No symbol for aimTransfer in aflr4AIM CAPS Info: No symbol for aimInterpolation in aflr4AIM CAPS Info: No symbol for aimInterpolateBar in aflr4AIM CAPS Info: No symbol for aimIntegration in aflr4AIM CAPS Info: No symbol for aimIntegrateBar in aflr4AIM CAPS Info: No symbol for aimSensitivity in aflr4AIM Analysis directory does not currently exist - it will be made automatically CAPS Info: No symbol for aimDiscr in aflr3AIM CAPS Info: No symbol for aimFreeDiscr in aflr3AIM CAPS Info: No symbol for aimLocateElement in aflr3AIM CAPS Info: No symbol for aimUsesDataSet in aflr3AIM CAPS Info: No symbol for aimCheck in aflr3AIM CAPS Info: No symbol for aimTransfer in aflr3AIM CAPS Info: No symbol for aimInterpolation in aflr3AIM CAPS Info: No symbol for aimInterpolateBar in aflr3AIM CAPS Info: No symbol for aimIntegration in aflr3AIM CAPS Info: No symbol for aimIntegrateBar in aflr3AIM CAPS Info: No symbol for aimSensitivity in aflr3AIM Analysis directory does not currently exist - it will be made automatically CAPS Info: No symbol for aimExecute in su2AIM CAPS Info: No symbol for aimCheck in su2AIM CAPS Info: No symbol for aimData in su2AIM CAPS Info: No symbol for aimSensitivity in su2AIM Analysis directory does not currently exist - it will be made automatically CAPS Info: No symbol for aimDiscr in egadsTessAIM CAPS Info: No symbol for aimFreeDiscr in egadsTessAIM CAPS Info: No symbol for aimLocateElement in egadsTessAIM CAPS Info: No symbol for aimUsesDataSet in egadsTessAIM CAPS Info: No symbol for aimCheck in egadsTessAIM CAPS Info: No symbol for aimTransfer in egadsTessAIM CAPS Info: No symbol for aimInterpolation in egadsTessAIM CAPS Info: No symbol for aimInterpolateBar in egadsTessAIM CAPS Info: No symbol for aimIntegration in egadsTessAIM CAPS Info: No symbol for aimIntegrateBar in egadsTessAIM CAPS Info: No symbol for aimSensitivity in egadsTessAIM Analysis directory does not currently exist - it will be made automatically CAPS Info: No symbol for aimExecute in astrosAIM CAPS Info: No symbol for aimCheck in astrosAIM CAPS Info: No symbol for aimData in astrosAIM CAPS Info: No symbol for aimSensitivity in astrosAIM --> enter ocsmBuild(buildTo=0) --> enter ocsmCheck() --> checks passed Interim EGADS version 1.19 (with OpenCASCADE 7.3.1) 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 0.521 1.3 restore 10 0.039 0.1 rule 1 0.068 0.2 intersect 1 3.767 9.5 subtract 1 4.313 10.9 union 1 29.872 75.6 join 1 0.092 0.2 extract 1 0.659 1.7 translate 2 0.021 0.1 rotatex 2 0.003 0.0 rotatey 1 0.002 0.0 scale 2 0.003 0.0 mirror 1 0.032 0.1 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 0.101 0.3 store 8 0.000 0.0 patbeg 1 0.000 0.0 patend 8 0.000 0.0 ifthen 57 0.001 0.0 else 4 0.000 0.0 endif 57 0.000 0.0 catbeg 1 0.000 0.0 mark 1 0.000 0.0 Total 313 39.498 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 2 Name = Wing, index = 1 Name = Farfield, index = 2 Getting mesh sizing parameters Mesh sizing name - Wing Mesh sizing name - Farfield Done getting mesh sizing parameters AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.13.13 AFLR2 : Version Date 10/10/20 @ 10:50PM AFLR2 : Compile OS Darwin 19.6.0 x86_64 AFLR2 : Compile Date 10/10/20 @ 10:50PM AFLR2 : Copyright 1994-2020, D.L. Marcum AFLR2 : --------------------------------------- AFLR4 : --------------------------------------- AFLR4 : AFLR4 LIBRARY AFLR4 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR4 : TRIA/QUAD SURFACE GRID GENERATOR AFLR4 : Version Number 10.11.10 AFLR4 : Version Date 10/30/20 @ 03:19PM AFLR4 : Compile OS Darwin 19.6.0 x86_64 AFLR4 : Compile Date 10/30/20 @ 03:19PM AFLR4 : Copyright 1994-2020, D.L. Marcum AFLR4 : --------------------------------------- EGADS : EGADS CAD Geometry Setup EGADS : Using EGADS Version 1.19 EGADS : Using OpenCASCADE Version ase with OpenCASCADE 7.3.1 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 = 0.298 seconds AFLR4 : GET EGADS TESS FROM AFLR4 DATA AFLR4 : EGADS TESS CREATED WITHOUT ERROR AFLR4 : CHECK COORDINATES OF EGADS TESSELLATION AFLR4 : CAD Definition= 1 Max Coordinate Deviation=0.000000e+00 AFLR4 : CAD Definition= 2 Max Coordinate Deviation=0.000000e+00 AFLR4 : CAD Definition= 3 Max Coordinate Deviation=0.000000e+00 AFLR4 : CAD Definition= 4 Max Coordinate Deviation=0.000000e+00 AFLR4 : CAD Definition= 5 Max Coordinate Deviation=0.000000e+00 AFLR4 : CAD Definition= 6 Max Coordinate Deviation=0.000000e+00 AFLR4 : CAD Definition= 1 Max Coordinate Deviation=0.000000e+00 AFLR4 : CAD Definition= 2 Max Coordinate Deviation=0.000000e+00 AFLR4 : CAD Definition= 3 Max Coordinate Deviation=0.000000e+00 AFLR4 : CAD Definition= 4 Max Coordinate Deviation=0.000000e+00 AFLR4 : CAD Definition= 5 Max Coordinate Deviation=0.000000e+00 AFLR4 : CAD Definition= 6 Max Coordinate Deviation=0.000000e+00 AFLR4 : COORDINATES OF EGADS TESSELLATION CHECKED WITHOUT ERROR AFLR4 : CHECK AFLR4 AND EGADS TRIA-FACE ORDERING AFLR4 : CAD Definition= 1 Ordering OK AFLR4 : CAD Definition= 2 Ordering OK AFLR4 : CAD Definition= 3 Ordering OK Reversed AFLR4 : CAD Definition= 4 Ordering OK Reversed AFLR4 : CAD Definition= 5 Ordering OK Reversed AFLR4 : CAD Definition= 6 Ordering OK AFLR4 : CAD Definition= 7 Ordering OK Reversed AFLR4 : CAD Definition= 8 Ordering OK AFLR4 : CAD Definition= 9 Ordering OK Reversed AFLR4 : CAD Definition= 10 Ordering OK AFLR4 : CAD Definition= 11 Ordering OK Reversed AFLR4 : CAD Definition= 12 Ordering OK AFLR4 : AFLR4 AND EGADS TRIA-FACE ORDERING CHECKED WITHOUT ERROR Body = 1 Number of nodes = 9015 Number of elements = 18026 Number of tris = 18026 Number of quad = 0 Body = 2 Number of nodes = 320 Number of elements = 636 Number of tris = 636 Number of quad = 0 ---------------------------- Total number of nodes = 9335 Total number of elements = 18662 Found link for groupMap (Attribute_Map) from parent Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 2 Name = Wing, index = 1 Name = Farfield, index = 2 Found link for a surface mesh (Surface_Mesh) from parent Number of surface nodes - 9335 Number of surface elements - 18662 Getting volume mesh UG PARAM : SETTING INPUT PARAMETERS FROM ARGUMENT VECTOR UG PARAM : mrecm = 3 UG PARAM : mrecqm = 3 AFLR3 : --------------------------------------- AFLR3 : AFLR3 LIBRARY AFLR3 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR3 : TETRAHEDRAL GRID GENERATOR AFLR3 : Version Number 16.30.16 AFLR3 : Version Date 10/10/20 @ 03:34PM AFLR3 : Compile OS Darwin 19.6.0 x86_64 AFLR3 : Compile Date 10/11/20 @ 12:50AM AFLR3 : Copyright 1994-2020, D.L. Marcum AFLR3 : --------------------------------------- AFLR3 IC : INPUT SURFACE GRID CHECK AFLR3 IC : Nodes, Elements = 9335 0 AFLR3 : CPU Time = 0.026 seconds AFLR3 IG : INITIAL VOLUME GRID GENERATION AFLR3 IG : Nodes, Elements = 9335 0 AFLR3 IG : Nodes, Elements = 8 10 AFLR3 IG : Nodes, Elements = 1868 12802 AFLR3 IG : Nodes, Elements = 3736 26174 AFLR3 IG : Nodes, Elements = 5604 39996 AFLR3 IG : Nodes, Elements = 7472 54696 AFLR3 IG : Nodes, Elements = 9340 70160 AFLR3 IG : Nodes, Elements = 9342 70214 AFLR3 IG : Nodes, Elements = 9342 70038 AFLR3 IG : Nodes, Elements = 9342 65457 AFLR3 IG : Nodes, Elements = 9342 63853 AFLR3 IG : Nodes, Elements = 9335 36678 AFLR3 IG : Nodes, Elements = 9335 42586 AFLR3 IG : Nodes, Elements = 9335 30432 AFLR3 IG : Nodes, Elements = 9335 28327 AFLR3 : CPU Time = 0.348 seconds AFLR3 GG : ISOTROPIC VOLUME GRID GENERATION AFLR3 GG : Nodes, Elements = 9335 28327 AFLR3 GG : Nodes, Elements = 13664 41383 AFLR3 GG : Nodes, Elements = 13664 58327 AFLR3 GG : Nodes, Elements = 13664 53926 AFLR3 GG : Nodes, Elements = 17251 65070 AFLR3 GG : Nodes, Elements = 17251 79156 AFLR3 GG : Nodes, Elements = 17251 74584 AFLR3 GG : Nodes, Elements = 20911 85936 AFLR3 GG : Nodes, Elements = 20911 100204 AFLR3 GG : Nodes, Elements = 20911 96106 AFLR3 GG : Nodes, Elements = 24578 107285 AFLR3 GG : Nodes, Elements = 24578 122135 AFLR3 GG : Nodes, Elements = 24578 118000 AFLR3 GG : Nodes, Elements = 28268 129223 AFLR3 GG : Nodes, Elements = 28268 143781 AFLR3 GG : Nodes, Elements = 28268 139869 AFLR3 GG : Nodes, Elements = 31926 150933 AFLR3 GG : Nodes, Elements = 31926 165332 AFLR3 GG : Nodes, Elements = 31926 161553 AFLR3 GG : Nodes, Elements = 35485 172289 AFLR3 GG : Nodes, Elements = 35485 186302 AFLR3 GG : Nodes, Elements = 35485 182688 AFLR3 GG : Nodes, Elements = 39014 193325 AFLR3 GG : Nodes, Elements = 39014 207191 AFLR3 GG : Nodes, Elements = 39014 203616 AFLR3 GG : Nodes, Elements = 42380 213746 AFLR3 GG : Nodes, Elements = 42380 226774 AFLR3 GG : Nodes, Elements = 42380 223470 AFLR3 GG : Nodes, Elements = 45594 233143 AFLR3 GG : Nodes, Elements = 45594 245701 AFLR3 GG : Nodes, Elements = 45594 242579 AFLR3 GG : Nodes, Elements = 48680 251862 AFLR3 GG : Nodes, Elements = 48680 263885 AFLR3 GG : Nodes, Elements = 48680 260843 AFLR3 GG : Nodes, Elements = 51607 269642 AFLR3 GG : Nodes, Elements = 51607 281129 AFLR3 GG : Nodes, Elements = 51607 278242 AFLR3 GG : Nodes, Elements = 54466 286829 AFLR3 GG : Nodes, Elements = 54466 298009 AFLR3 GG : Nodes, Elements = 54466 295289 AFLR3 GG : Nodes, Elements = 57175 303426 AFLR3 GG : Nodes, Elements = 57175 314032 AFLR3 GG : Nodes, Elements = 57175 311347 AFLR3 GG : Nodes, Elements = 59734 319030 AFLR3 GG : Nodes, Elements = 59734 329059 AFLR3 GG : Nodes, Elements = 59734 326537 AFLR3 GG : Nodes, Elements = 62197 333935 AFLR3 GG : Nodes, Elements = 62197 343560 AFLR3 GG : Nodes, Elements = 62197 341234 AFLR3 GG : Nodes, Elements = 64493 348127 AFLR3 GG : Nodes, Elements = 64493 357104 AFLR3 GG : Nodes, Elements = 64493 354919 AFLR3 GG : Nodes, Elements = 66655 361408 AFLR3 GG : Nodes, Elements = 66655 369771 AFLR3 GG : Nodes, Elements = 66655 367737 AFLR3 GG : Nodes, Elements = 68691 373851 AFLR3 GG : Nodes, Elements = 68691 381683 AFLR3 GG : Nodes, Elements = 68691 379827 AFLR3 GG : Nodes, Elements = 70623 385623 AFLR3 GG : Nodes, Elements = 70623 393122 AFLR3 GG : Nodes, Elements = 70623 391269 AFLR3 GG : Nodes, Elements = 72365 396500 AFLR3 GG : Nodes, Elements = 72365 403287 AFLR3 GG : Nodes, Elements = 72365 401668 AFLR3 GG : Nodes, Elements = 74030 406665 AFLR3 GG : Nodes, Elements = 74030 413119 AFLR3 GG : Nodes, Elements = 74030 411573 AFLR3 GG : Nodes, Elements = 75529 416071 AFLR3 GG : Nodes, Elements = 75529 421907 AFLR3 GG : Nodes, Elements = 75529 420507 AFLR3 GG : Nodes, Elements = 76869 424529 AFLR3 GG : Nodes, Elements = 76869 429740 AFLR3 GG : Nodes, Elements = 76869 428485 AFLR3 GG : Nodes, Elements = 78055 432045 AFLR3 GG : Nodes, Elements = 78055 436697 AFLR3 GG : Nodes, Elements = 78055 435531 AFLR3 GG : Nodes, Elements = 79029 438454 AFLR3 GG : Nodes, Elements = 79029 442292 AFLR3 GG : Nodes, Elements = 79029 441330 AFLR3 GG : Nodes, Elements = 79832 443739 AFLR3 GG : Nodes, Elements = 79832 446926 AFLR3 GG : Nodes, Elements = 79832 446120 AFLR3 GG : Nodes, Elements = 80482 448071 AFLR3 GG : Nodes, Elements = 80482 450702 AFLR3 GG : Nodes, Elements = 80482 449971 AFLR3 GG : Nodes, Elements = 80956 451393 AFLR3 GG : Nodes, Elements = 80956 453377 AFLR3 GG : Nodes, Elements = 80956 452794 AFLR3 GG : Nodes, Elements = 81261 453709 AFLR3 GG : Nodes, Elements = 81261 454931 AFLR3 GG : Nodes, Elements = 81261 454583 AFLR3 GG : Nodes, Elements = 81421 455063 AFLR3 GG : Nodes, Elements = 81421 455738 AFLR3 GG : Nodes, Elements = 81421 455501 AFLR3 GG : Nodes, Elements = 81492 455714 AFLR3 GG : Nodes, Elements = 81492 456042 AFLR3 GG : Nodes, Elements = 81492 455920 AFLR3 GG : Nodes, Elements = 81521 456007 AFLR3 GG : Nodes, Elements = 81521 456151 AFLR3 GG : Nodes, Elements = 81521 456083 AFLR3 GG : Nodes, Elements = 81534 456122 AFLR3 GG : Nodes, Elements = 81534 456170 AFLR3 GG : Nodes, Elements = 81534 456152 AFLR3 GG : Nodes, Elements = 81539 456167 AFLR3 GG : Nodes, Elements = 81539 456190 AFLR3 GG : Nodes, Elements = 81539 456179 AFLR3 GG : Nodes, Elements = 81543 456191 AFLR3 GG : Nodes, Elements = 81543 456211 AFLR3 GG : Nodes, Elements = 81543 456201 AFLR3 : CPU Time = 3.917 seconds AFLR3 QI : QUALITY IMPROVEMENT AFLR3 QI : Nodes, Elements = 81543 456201 AFLR3 QI : Nodes, Elements = 81135 453919 AFLR3 QI : Nodes, Elements = 81090 453671 AFLR3 QI : Nodes, Elements = 81087 453656 AFLR3 QI : Nodes, Elements = 81087 455570 AFLR3 QI : Nodes, Elements = 81087 453362 AFLR3 QI : Nodes, Elements = 81087 452458 AFLR3 QI : Nodes, Elements = 81087 452731 AFLR3 QI : Nodes, Elements = 81087 452270 AFLR3 QI : Nodes, Elements = 81087 452172 AFLR3 QI : Nodes, Elements = 81087 452375 AFLR3 QI : Nodes, Elements = 81087 452167 AFLR3 QI : Nodes, Elements = 81087 452128 AFLR3 : CPU Time = 1.043 seconds AFLR3 : DONE UG3 : DIHEDRAL ANGLE CHECK UG3 : No. Tet Elems = 452128 UG3 : Min, Max Ang = 12.75 157.7 UG3 : Average Angle = 70.2 UG3 : No. Angle>160.0 = 0 UG3 : No. Angle>179.9 = 0 UG3 : VOL CHECK UG3 : Total-Volume = 3.72e+06 UG3 : No. Tet Elems = 452128 UG3 : Min Vol = 1.3e-06 UG3 : Average Vol = 8.22 UG3 : Total-Tet-Vol = 3.72e+06 UG3 : No. Vol<TOL = 0 UG3 : Q VOL-LENGTH-RATIO CHECK 2/3 2 UG3 : Q = c * Vol / sum( L ) UG3 : 0 <= Q <= 1 UG3 : No. Tet Elems = 452128 UG3 : Min, Max Q = 0.215 1 UG3 : Average Q = 0.9 UG3 : No. Q< 0.1 = 0 UG3 : No. Q< 0.01 = 0 Volume mesh: Number of nodes = 81087 Number of elements = 470790 Number of triangles = 18662 Number of quadrilatarals = 0 Number of tetrahedrals = 452128 Number of pyramids= 0 Number of prisms= 0 Number of hexahedrals= 0 No project name ("Proj_Name") provided - A volume mesh will not be written out Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 5 Name = wingSpar1, index = 1 Name = riteWingSkin, index = 2 Name = wingRib, index = 3 Name = leftWingSkin, index = 4 Name = wingSpar2, index = 5 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = wingSpar1, index = 1 Name = wingSpar2, index = 2 Name = leadingEdge, index = 3 Name = rootLeadingEdge, index = 4 Getting surface mesh for body 1 (of 1) Tessellating body Number of nodes = 265 Number of elements = 346 Number of node elements = 0 Number of line elements = 0 Number of triangle elements = 0 Number of quadrilateral elements = 346 ---------------------------- Total number of nodes = 265 Total number of elements = 346 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. 81087 points. 2 surface markers. +------------------------------------+ | Index| Marker| Elements| +------------------------------------+ | 0| 1| 18026| | 1| 2| 636| +------------------------------------+ 452128 tetrahedra. ------------------------- Geometry Preprocessing ------------------------ Setting point connectivity. Renumbering points (Reverse Cuthill McKee Ordering). Recomputing point connectivity. Setting element connectivity. Checking the numerical grid orientation. Identifying edges and vertices. Computing centers of gravity. Setting the control volume structure. Volume of the computational grid: 3.72e+06. Finding max control volume width. Searching for the closest normal neighbors to the surfaces. Storing a mapping from global to local point index. Compute the surface curvature. Max K: 433. Mean K: 20.4. Standard deviation K: 49.2. Checking for periodicity. Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 81087| 1/1.00| 10| | 1| 13391| 1/6.06| 8.23| | 2| 2049| 1/6.54| 6.6| +-------------------------------------------+ Semi-span length = 3.87 m. Wetted area = 20.6 m^2. Area projection in the x-plane = 1.53 m^2, y-plane = 0.869 m^2, z-plane = 9.83 m^2. Max. coordinate in the x-direction = 2.37 m, y-direction = 3.87 m, z-direction = 0.4 m. Min coordinate in the x-direction = 0 m, y-direction = -3.87 m, z-direction = -0.0329 m. ------------------------- Driver information -------------------------- A Fluid driver has been instantiated. ------------------------ Iteration Preprocessing ------------------------ Zone 1: Euler/Navier-Stokes/RANS fluid iteration. ------------------------- Solver Preprocessing -------------------------- Inviscid flow: Computing density based on free-stream temperature and pressure using the ideal gas law. Force coefficients computed using free-stream values. -- Models: +------------------------------------------------------------------------------+ | Viscosity Model| Conductivity Model| Fluid Model| +------------------------------------------------------------------------------+ | -| -| STANDARD_AIR| +------------------------------------------------------------------------------+ -- Fluid properties: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Gas Constant| 287.058| 1| N.m/kg.K| 287.058| | Spec. Heat Ratio| -| -| -| 1.4| +------------------------------------------------------------------------------+ -- Initial and free-stream conditions: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Static Pressure| 101325| 1| Pa| 101325| | Density| 1.22498| 1| kg/m^3| 1.22498| | Temperature| 288.15| 1| K| 288.15| | Total Energy| 211798| 1| m^2/s^2| 211798| | Velocity-X| 100.087| 1| m/s| 100.087| | Velocity-Y| 0| 1| m/s| 0| | Velocity-Z| 0| 1| m/s| 0| | Velocity Magnitude| 100.087| 1| m/s| 100.087| +------------------------------------------------------------------------------+ | Mach Number| -| -| -| 0.294118| +------------------------------------------------------------------------------+ Initialize Jacobian structure (Euler). MG level: 0. Initialize Jacobian structure (Euler). MG level: 1. Initialize Jacobian structure (Euler). MG level: 2. ----------------- Integration and Numerics Preprocessing ---------------- Integration Preprocessing. Numerics Preprocessing. ---------------------- Python Interface Preprocessing --------------------- Setting customized boundary conditions for zone 0 ------------------------------ Begin Solver ----------------------------- ------------------------ Evaluate Special Output ------------------------ Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat). ------------------------------------------------------------------------- ---------------------- Local Time Stepping Summary ---------------------- MG level: 0 -> Min. DT: 4.75954e-05. Max. DT: 0.133844. CFL: 10. MG level: 1 -> Min. DT: 9.01528e-05. Max. DT: 0.192401. CFL: 8.2296. MG level: 2 -> Min. DT: 0.000145445. Max. DT: 0.249416. CFL: 6.60257. ------------------------------------------------------------------------- ----------------------- Residual Evolution Summary ---------------------- log10[Maximum residual]: -0.734914. Maximum residual point 2283, located at (1.25039, -0.895465, 0.208146). ------------------------------------------------------------------------- Iter Time(s) Res[Rho] Res[RhoE] CL(Total) CD(Total) 0 7.213056 -1.764585 3.704520 -0.192437 0.438788 1 7.041535 -1.665379 3.813117 0.033126 0.242902 2 7.063759 -1.655562 3.824904 0.168188 0.077505 3 6.993388 -1.751945 3.727511 0.205416 0.022590 ------------------------ Evaluate Special Output ------------------------ Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat). ------------------------------------------------------------------------- 4 7.000459 -1.820189 3.650994 0.209024 0.012775 ----------------------------- Solver Exit ------------------------------- Maximum number of external iterations reached (EXT_ITER). ------------------------------------------------------------------------- -------------------------- File Output Summary -------------------------- Writing comma-separated values (CSV) surface files. Loading solution output data locally on each rank. Sorting output data across all ranks. Writing binary SU2 native restart file. Preparing element connectivity across all ranks. Writing Tecplot ASCII file volume solution file. Writing Tecplot ASCII file surface solution file. ------------------------------------------------------------------------- ------------------------- Solver Postprocessing ------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterpolator container. Deleted CTransfer container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ ==> Running SU2 post-analysis... Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv Number of variables = 7 Number of data points = 9015 Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv Number of variables = 7 Number of data points = 9015 Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv Number of variables = 7 Number of data points = 9015 Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv Number of variables = 7 Number of data points = 9015 Executing dataTransfer "Pressure"...... Bound upperWing: Normalized Integrated Pressure Rank=0: src=6.265700e+09, tgt=6.265700e+09, diff=3.835140e+01 Bound lowerWing: Normalized Integrated Pressure Rank=0: src=6.102777e+09, tgt=6.102777e+09, diff=1.228010e+01 Bound leftTip: Normalized Integrated Pressure Rank=0: src=6.123320e+07, tgt=6.123320e+07, diff=0.000000e+00 Bound riteTip: Normalized Integrated Pressure Rank=0: src=6.125526e+07, tgt=6.125526e+07, diff=0.000000e+00 ==> Running ASTROS pre-analysis... Getting FEA materials....... Number of materials - 2 Material name - Unobtainium No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic" Material name - Madeupium Done getting FEA materials Getting FEA properties....... Number of properties - 5 Property name - leftWingSkin Property name - riteWingSkin Property name - wingRib Property name - wingSpar1 Property name - wingSpar2 Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - rootConstraint No "constraintType" specified for Constraint tuple rootConstraint, defaulting to "ZeroDisplacement" Done getting FEA constraints Support tuple is NULL - No supports applied Connect tuple is NULL - Using defaults Getting FEA loads....... Number of loads - 1 Load name - pressureAero No "groupName" specified for Load tuple pressureAero, going to use load name Done getting FEA loads Extracting external pressure loads from data transfer.... TransferName = upperWing Number of Elements = 96 (total = 96) TransferName = lowerWing Number of Elements = 96 (total = 192) TransferName = leftTip Number of Elements = 10 (total = 202) TransferName = riteTip Number of Elements = 10 (total = 212) Design_Variable tuple is NULL - No design variables applied Design_Constraint tuple is NULL - No design constraints applied Analysis tuple is NULL Getting FEA analyses....... Number of analyses - 1 Analysis name - Default Done getting FEA analyses Writing Astros grid and connectivity file (in large field format) .... Finished writing Astros grid file Writing subElement types (if any) - appending mesh file Writing Astros instruction file.... Writing analysis cards Writing load ADD cards Writing constraint cards--each subcase individually Writing load cards Writing material cards Writing property cards Writing coordinate system cards Running Astros...... ==> Running ASTROS post-analysis... Executing dataTransfer "Displacement"...... ==> Running SU2 pre-analysis... Getting CFD boundary conditions Boundary condition name - Wing Boundary condition name - Farfield Done getting CFD boundary conditions Found link for volume mesh (Volume_Mesh) from parent Writing boundary flags - bcProps.surfaceProp[0].surfaceType = 1 - bcProps.surfaceProp[1].surfaceType = 3 Done boundary flags Writing SU2 data transfer files Writing SU2 Motion File - aeroelasticIterative_motion.dat Warning: The su2 cfg file will be overwritten! Write SU2 configuration file for version "Falcon" Running SU2...... ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 6.2.0 "Falcon" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Mesh Deformation Code) | | | ------------------------------------------------------------------------- | The current SU2 release has been coordinated by the | | SU2 International Developers Society <www.su2devsociety.org> | | with selected contributions from the open-source community. | ------------------------------------------------------------------------- | The main research teams contributing to the current release are: | | - Prof. Juan J. Alonso's group at Stanford University. | | - Prof. Piero Colonna's group at Delft University of Technology. | | - Prof. Nicolas R. Gauger's group at Kaiserslautern U. of Technology. | | - Prof. Alberto Guardone's group at Polytechnic University of Milan. | | - Prof. Rafael Palacios' group at Imperial College London. | | - Prof. Vincent Terrapon's group at the University of Liege. | | - Prof. Edwin van der Weide's group at the University of Twente. | | - Lab. of New Concepts in Aeronautics at Tech. Inst. of Aeronautics. | ------------------------------------------------------------------------- | Copyright 2012-2019, Francisco D. Palacios, Thomas D. Economon, | | Tim Albring, and the SU2 contributors. | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see <http://www.gnu.org/licenses/>. | ------------------------------------------------------------------------- ------------------------ Physical Case Definition ----------------------- Input mesh file name: aeroelasticIterative.su2 ---------------------- Grid deformation parameters ---------------------- Grid deformation using a linear elasticity method. -------------------------- Output Information --------------------------- Output mesh file name: aeroelasticIterative.su2. A file will be created to visualize the surface deformation. No file for visualizing the deformation. Cell stiffness scaled by distance to nearest solid surface. ------------------- Config File Boundary Information -------------------- +-----------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------+ | Euler wall| 1| +-----------------------------------------+ | Far-field| 2| +-----------------------------------------+ ---------------------- Read Grid File Information ----------------------- Three dimensional problem. 81087 points. 2 surface markers. +------------------------------------+ | Index| Marker| Elements| +------------------------------------+ | 0| 1| 18026| | 1| 2| 636| +------------------------------------+ 452128 tetrahedra. ----------------------- Preprocessing computations ---------------------- Setting local point connectivity. Checking the numerical grid orientation of the interior elements. Identify edges and vertices. Computing centers of gravity. Setting the bound control volume structure. Merging grid connectivity. Merging grid coordinates. Writing surface mesh file. Writing .csv surface file. --------------------- Surface grid deformation (ZONE 0) ----------------- Performing the deformation of the surface grid. Updating the surface coordinates from the input file. ------------------- Volumetric grid deformation (ZONE 0) ---------------- Performing the deformation of the volumetric grid. Computing volumes of the grid elements. Min. volume: 1.30476e-06, max. volume: 4674.72. Min. distance: 0.0169992, max. distance: 132.146. # ILU preconditioner. # FGMRES residual history # Residual tolerance target = 1e-14 # Initial residual norm = 9.16407 0 1 10 0.00155824 20 3.18792e-05 30 3.50089e-06 40 5.87318e-07 50 6.30209e-08 60 2.96425e-09 70 1.19536e-10 80 4.5298e-12 90 1.70459e-13 100 3.4549e-14 110 3.41787e-14 120 3.41782e-14 130 3.41782e-14 140 3.41782e-14 150 3.41782e-14 160 3.4178e-14 170 3.40842e-14 180 1.01469e-14 # FGMRES final (true) residual: # Iteration = 181: |res|/|res0| = 7.22885e-15. Computing volumes of the grid elements. Non-linear iter.: 1/3. Linear iter.: 181. Min. volume: 1.10182. Error: 6.62457e-14. Computing volumes of the grid elements. Min. volume: 1.10182, max. volume: 4.74616e+10. Min. distance: 5.94616, max. distance: 12981.8. # ILU preconditioner. # FGMRES residual history # Residual tolerance target = 1e-14 # Initial residual norm = 48839.3 0 1 10 0.0172596 20 0.00656348 30 0.0052419 40 0.00458997 50 0.00423714 60 0.00338602 70 0.0027945 80 0.00246721 90 0.00213281 100 0.00194204 110 0.00179877 120 0.00156923 130 0.00139906 140 0.00128912 150 0.00110253 160 0.00101327 170 0.000960892 180 0.000930668 190 0.000858323 200 0.000756167 210 0.000695957 220 0.00065794 230 0.000632314 240 0.000533506 250 0.000457424 260 0.000417523 270 0.000394051 280 0.000354236 290 0.000325071 300 0.00030562 310 0.000290014 320 0.000279709 330 0.000267702 340 0.00025164 350 0.000230824 360 0.000222094 370 0.00020893 380 0.000198551 390 0.000189368 400 0.00017944 410 0.000170909 420 0.000163892 430 0.000158617 440 0.000154734 450 0.000149422 460 0.000146487 470 0.000142602 480 0.00014032 490 0.000137847 500 0.000133215 # FGMRES final (true) residual: # Iteration = 500: |res|/|res0| = 0.000133215. # WARNING in CSysSolve::FGMRES_LinSolver(): # true residual norm and calculated residual norm do not agree. # res = 6.50611, beta = 6.50611, tol = 1e-13. # res - beta = -8.43561e-10 Computing volumes of the grid elements. Non-linear iter.: 2/3. Linear iter.: 500. Min. volume: 9.22425. Error: 6.50611. Computing volumes of the grid elements. Min. volume: 9.22425, max. volume: 4.43428e+12. Min. distance: 5.31225, max. distance: 82015.9. # ILU preconditioner. # FGMRES residual history # Residual tolerance target = 1e-14 # Initial residual norm = 213596 0 1 10 0.00691684 20 0.00342507 30 0.00309836 40 0.00190232 50 0.00109431 60 0.000978095 70 0.000809669 80 0.000674122 90 0.000642966 100 0.000614516 110 0.000578899 120 0.000545137 130 0.00047504 140 0.000423851 150 0.000361958 160 0.000328967 170 0.000300885 180 0.000276548 190 0.000257637 200 0.000237684 210 0.000222505 220 0.000204972 230 0.000174734 240 0.000154294 250 0.000136919 260 0.00012493 270 0.000113848 280 0.000105656 290 9.91436e-05 300 9.1966e-05 310 8.12542e-05 320 7.6366e-05 330 7.08111e-05 340 6.69945e-05 350 6.22682e-05 360 5.78776e-05 370 5.39313e-05 380 5.23153e-05 390 4.94033e-05 400 4.7774e-05 410 4.59885e-05 420 4.45118e-05 430 4.33685e-05 440 4.19876e-05 450 4.06102e-05 460 3.98628e-05 470 3.86985e-05 480 3.76313e-05 490 3.70229e-05 500 3.67184e-05 # FGMRES final (true) residual: # Iteration = 500: |res|/|res0| = 3.67184e-05. # WARNING in CSysSolve::FGMRES_LinSolver(): # true residual norm and calculated residual norm do not agree. # res = 7.84291, beta = 7.84291, tol = 1e-13. # res - beta = -3.04059e-09 Computing volumes of the grid elements. Non-linear iter.: 3/3. Linear iter.: 500. Min. volume: 2.43405. Error: 7.84291. ----------------------- Write deformed grid files ----------------------- Merging grid connectivity. Merging grid coordinates. Writing surface mesh file. Writing .su2 file. Writing .stl surface file. Writing .csv surface file. Adding any FFD information to the SU2 file. ------------------------- Solver Postprocessing ------------------------- Deleted CGeometry container. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted COutput class. Completed in 233.063862 seconds on 1 core. ------------------------- Exit Success (SU2_DEF) ------------------------ ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 6.2.0 "Falcon" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Computational Fluid Dynamics Code) | | | ------------------------------------------------------------------------- | The current SU2 release has been coordinated by the | | SU2 International Developers Society <www.su2devsociety.org> | | with selected contributions from the open-source community. | ------------------------------------------------------------------------- | The main research teams contributing to the current release are: | | - Prof. Juan J. Alonso's group at Stanford University. | | - Prof. Piero Colonna's group at Delft University of Technology. | | - Prof. Nicolas R. Gauger's group at Kaiserslautern U. of Technology. | | - Prof. Alberto Guardone's group at Polytechnic University of Milan. | | - Prof. Rafael Palacios' group at Imperial College London. | | - Prof. Vincent Terrapon's group at the University of Liege. | | - Prof. Edwin van der Weide's group at the University of Twente. | | - Lab. of New Concepts in Aeronautics at Tech. Inst. of Aeronautics. | ------------------------------------------------------------------------- | Copyright 2012-2019, Francisco D. Palacios, Thomas D. Economon, | | Tim Albring, and the SU2 contributors. | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see <http://www.gnu.org/licenses/>. | ------------------------------------------------------------------------- ------------------------ Physical Case Definition ----------------------- Compressible Euler equations. Mach number: 0.294118. Angle of attack (AoA): 0 deg, and angle of sideslip (AoS): 0 deg. No restart solution, use the values at infinity (freestream). Dimensional simulation. The reference area is 10 m^2. The semi-span will be computed using the max y(3D) value. The reference length is 7.74597 m. Reference origin for moment evaluation is (0.322749, 0, 0). Surface(s) where the force coefficients are evaluated: 1. Surface(s) plotted in the output file: 1. Surface(s) affected by the design variables: 1. Input mesh file name: aeroelasticIterative.su2 ---------------------- Space Numerical Integration ---------------------- Roe (with entropy fix = 0.001) solver for the flow inviscid terms. Roe with DDES's FD low-dissipation function. Second order integration in space, with slope limiter. Venkatakrishnan slope-limiting method, with constant: 0.05. The reference element size is: 1. Gradient computation using Green-Gauss theorem. ---------------------- Time Numerical Integration ----------------------- Local time stepping (steady state simulation). Euler implicit method for the flow equations. FGMRES is used for solving the linear system. Using a ILU(0) preconditioning. Convergence criteria of the linear solver: 1e-06. Max number of linear iterations: 10. V Multigrid Cycle, with 2 multigrid levels. Damping factor for the residual restriction: 0.75. Damping factor for the correction prolongation: 0.75. No CFL adaptation. +-------------------------------------------+ | MG Level| Presmooth|PostSmooth|CorrectSmo| +-------------------------------------------+ | 0| 1| 0| 0| | 1| 2| 0| 0| | 2| 3| 0| 0| +-------------------------------------------+ Courant-Friedrichs-Lewy number: 10 ------------------------- Convergence Criteria -------------------------- Maximum number of iterations: 5. Reduce the density residual 6 orders of magnitude. The minimum bound for the density residual is 10^(-8). Start convergence criteria at iteration 10. -------------------------- Output Information --------------------------- Writing a solution file every 1000 iterations. Writing the convergence history every 1 iterations. The output file format is Tecplot ASCII (.dat). Convergence history file name: history_aeroelasticIterative. Forces breakdown file name: forces_breakdown_aeroelasticIterative.dat. Surface flow coefficients file name: surface_flow_aeroelasticIterative. Flow variables file name: flow_aeroelasticIterative. Restart flow file name: restart_flow_aeroelasticIterative.dat. ------------------- Config File Boundary Information -------------------- +-----------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------+ | Euler wall| 1| +-----------------------------------------+ | Far-field| 2| +-----------------------------------------+ ---------------------- Read Grid File Information ----------------------- Three dimensional problem. 81087 points. 2 surface markers. +------------------------------------+ | Index| Marker| Elements| +------------------------------------+ | 0| 1| 18026| | 1| 2| 636| +------------------------------------+ 452128 tetrahedra. ------------------------- Geometry Preprocessing ------------------------ Setting point connectivity. Renumbering points (Reverse Cuthill McKee Ordering). Recomputing point connectivity. Setting element connectivity. Checking the numerical grid orientation. There has been a re-orientation of the TETRAHEDRON volume elements. There has been a re-orientation of the TRIANGLE surface elements. Identifying edges and vertices. Computing centers of gravity. Setting the control volume structure. Volume of the computational grid: 6.56e+18. 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: 2.53. Mean K: 0.00739. Standard deviation K: 0.0489. Checking for periodicity. Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 81087| 1/1.00| 10| | 1| 13393| 1/6.05| 8.23| | 2| 2068| 1/6.48| 6.62| +-------------------------------------------+ Semi-span length = 3.16e+04 m. Wetted area = 2.05e+10 m^2. Area projection in the x-plane = 8.7e+09 m^2, y-plane = 6.37e+09 m^2, z-plane = 6e+08 m^2. Max. coordinate in the x-direction = 1.43e+03 m, y-direction = 3.16e+04 m, z-direction = 0.168 m. Min coordinate in the x-direction = -1.5e+04 m, y-direction = -3.31e+04 m, z-direction = -3.63e+05 m. ------------------------- Driver information -------------------------- A Fluid driver has been instantiated. ------------------------ Iteration Preprocessing ------------------------ Zone 1: Euler/Navier-Stokes/RANS fluid iteration. ------------------------- Solver Preprocessing -------------------------- Inviscid flow: Computing density based on free-stream temperature and pressure using the ideal gas law. Force coefficients computed using free-stream values. -- Models: +------------------------------------------------------------------------------+ | Viscosity Model| Conductivity Model| Fluid Model| +------------------------------------------------------------------------------+ | -| -| STANDARD_AIR| +------------------------------------------------------------------------------+ -- Fluid properties: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Gas Constant| 287.058| 1| N.m/kg.K| 287.058| | Spec. Heat Ratio| -| -| -| 1.4| +------------------------------------------------------------------------------+ -- Initial and free-stream conditions: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Static Pressure| 101325| 1| Pa| 101325| | Density| 1.22498| 1| kg/m^3| 1.22498| | Temperature| 288.15| 1| K| 288.15| | Total Energy| 211798| 1| m^2/s^2| 211798| | Velocity-X| 100.087| 1| m/s| 100.087| | Velocity-Y| 0| 1| m/s| 0| | Velocity-Z| 0| 1| m/s| 0| | Velocity Magnitude| 100.087| 1| m/s| 100.087| +------------------------------------------------------------------------------+ | Mach Number| -| -| -| 0.294118| +------------------------------------------------------------------------------+ Initialize Jacobian structure (Euler). MG level: 0. Initialize Jacobian structure (Euler). MG level: 1. Initialize Jacobian structure (Euler). MG level: 2. ----------------- Integration and Numerics Preprocessing ---------------- Integration Preprocessing. Numerics Preprocessing. ---------------------- Python Interface Preprocessing --------------------- Setting customized boundary conditions for zone 0 ------------------------------ Begin Solver ----------------------------- ------------------------ Evaluate Special Output ------------------------ Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat). ------------------------------------------------------------------------- ---------------------- Local Time Stepping Summary ---------------------- MG level: 0 -> Min. DT: 0.00113057. Max. DT: 4116.12. CFL: 10. MG level: 1 -> Min. DT: 0.0425715. Max. DT: 6422.43. CFL: 8.23001. MG level: 2 -> Min. DT: 0.117405. Max. DT: 30848.2. CFL: 6.62291. ------------------------------------------------------------------------- ----------------------- Residual Evolution Summary ---------------------- log10[Maximum residual]: 14.2119. Maximum residual point 41987, located at (1.66016e+06, 678158, 216711). There are 43307 non-physical points in the solution. ------------------------------------------------------------------------- Iter Time(s) Res[Rho] Res[RhoE] CL(Total) CD(Total) 0 5.986575 12.008572 17.477678 -10000.000000 10000.000000 1 6.164688 12.895313 18.253730 10000.000000 -10000.000000 2 6.330889 13.224554 18.775217 10000.000000 10000.000000 3 6.385863 13.536751 19.124587 10000.000000 -10000.000000 ------------------------ Evaluate Special Output ------------------------ Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat). ------------------------------------------------------------------------- 4 6.476579 13.870099 20.581584 -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 53056 non-physical points in the solution. Warning: 1306 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=9.544332e+12, tgt=9.544312e+12, diff=1.958909e+07 Bound lowerWing: Normalized Integrated Pressure Rank=0: src=1.425842e+12, tgt=1.425838e+12, diff=3.403976e+06 Bound leftTip: Normalized Integrated Pressure Rank=0: src=1.568085e+10, tgt=1.568085e+10, diff=0.000000e+00 Bound riteTip: Normalized Integrated Pressure Rank=0: src=2.299734e+10, tgt=2.299734e+10, diff=2.237934e+01 ==> 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 7m21.407s user 7m37.564s sys 0m9.655s + status=0 + set +x ================================================= data/session11/aeroelastic_Iterative_SU2_Astros.py passed (as expected) ================================================= ************************************************* ************************************************* All tests pass! ================================================= ================================================= [Execution node] check if [macys] is in [[windows10x64, windows7x64]] Run condition [Execution node ] preventing perform for step [Execute Windows batch command] [GNU C Compiler (gcc)] Sleeping for 5 seconds due to JENKINS-32191... [GNU C Compiler (gcc)] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_QuickTestCaps/7.3/CAPS/training/DARWIN64') [GNU C Compiler (gcc)] Successfully parsed console log [GNU C Compiler (gcc)] -> found 0 issues (skipped 0 duplicates) [GNU C Compiler (gcc)] Skipping post processing [GNU C Compiler (gcc)] No filter has been set, publishing all 0 issues [GNU C Compiler (gcc)] Repository miner is not configured, skipping mining [Clang (LLVM based)] Sleeping for 5 seconds due to JENKINS-32191... [Clang (LLVM based)] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_QuickTestCaps/7.3/CAPS/training/DARWIN64') [Clang (LLVM based)] Successfully parsed console log [Clang (LLVM based)] -> found 0 issues (skipped 0 duplicates) [Clang (LLVM based)] Skipping post processing [Clang (LLVM based)] No filter has been set, publishing all 0 issues [Clang (LLVM based)] Repository miner is not configured, skipping mining [Static Analysis] Reference build recorder is not configured [Static Analysis] Obtaining reference build from same job (7.3,DARWIN64,macys) [Static Analysis] Using reference build 'ESP_QuickTestCaps/CASREV=7.3,ESP_ARCH=DARWIN64,buildnode=macys #23' to compute new, fixed, and outstanding issues [Static Analysis] Issues delta (vs. reference build): outstanding: 0, new: 0, fixed: 0 [Static Analysis] Evaluating quality gates [Static Analysis] -> PASSED - Total (any severity): 0 - Quality QualityGate: 1 [Static Analysis] -> All quality gates have been passed [Static Analysis] Health report is disabled - skipping [Static Analysis] Created analysis result for 0 issues (found 0 new issues, fixed 0 issues) [Static Analysis] Attaching ResultAction with ID 'analysis' to build 'ESP_QuickTestCaps/CASREV=7.3,ESP_ARCH=DARWIN64,buildnode=macys #24'. [Checks API] No suitable checks publisher found. [PostBuildScript] - [INFO] Executing post build scripts. [PostBuildScript] - [INFO] build step #0 should only be executed on MATRIX [WS-CLEANUP] Deleting project workspace... [WS-CLEANUP] done Finished: SUCCESS