Skipping 2,912 KB..
Full Log 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 0.437 0.5
restore 12 0.036 0.0
rule 1 0.052 0.1
intersect 4 23.035 25.5
subtract 1 18.418 20.4
union 1 47.521 52.7
join 1 0.093 0.1
extract 1 0.552 0.6
translate 2 0.013 0.0
rotatex 2 0.003 0.0
rotatey 1 0.001 0.0
scale 2 0.003 0.0
mirror 1 0.018 0.0
interface 4 0.000 0.0
end 4 0.000 0.0
set 77 0.002 0.0
udparg 3 0.000 0.0
select 26 0.048 0.1
store 7 0.000 0.0
patbeg 2 0.000 0.0
patend 11 0.001 0.0
ifthen 48 0.001 0.0
else 2 0.000 0.0
endif 48 0.000 0.0
catbeg 1 0.000 0.0
catend 1 0.000 0.0
mark 2 0.000 0.0
group 1 0.000 0.0
Total 284 90.239
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 1m23.576s
user 0m51.799s
sys 0m39.256s
+ status=0
+ set +x
=================================================
data/session10/nastran_5_Flutter.py passed (as expected)
=================================================
=================================================
aeroelastic_Iterative_SU2_Astros.py test;
+ python aeroelastic_Iterative_SU2_Astros.py
+ tee -a /Users/jenkins/workspace/ESP_QuickTestCaps/7.4/CAPS/training/DARWIN64/CAPS/training/training.log
Definition of "kt" in "/Users/jenkins/workspace/ESP_QuickTestCaps/7.4/CAPS/training/DARWIN64/ESP/udunits/udunits2-common.xml", line 90, overrides prefixed-unit "1000000 kilogram"
Definition of "microns" in "/Users/jenkins/workspace/ESP_QuickTestCaps/7.4/CAPS/training/DARWIN64/ESP/udunits/udunits2-common.xml", line 336, overrides prefixed-unit "1e-15 second"
Definition of "ft" in "/Users/jenkins/workspace/ESP_QuickTestCaps/7.4/CAPS/training/DARWIN64/ESP/udunits/udunits2-common.xml", line 433, overrides prefixed-unit "1e-12 kilogram"
Definition of "yd" in "/Users/jenkins/workspace/ESP_QuickTestCaps/7.4/CAPS/training/DARWIN64/ESP/udunits/udunits2-common.xml", line 441, overrides prefixed-unit "8.64e-20 second"
Definition of "pt" in "/Users/jenkins/workspace/ESP_QuickTestCaps/7.4/CAPS/training/DARWIN64/ESP/udunits/udunits2-common.xml", line 655, overrides prefixed-unit "1e-09 kilogram"
Definition of "at" in "/Users/jenkins/workspace/ESP_QuickTestCaps/7.4/CAPS/training/DARWIN64/ESP/udunits/udunits2-common.xml", line 1052, overrides prefixed-unit "1e-15 kilogram"
Definition of "ph" in "/Users/jenkins/workspace/ESP_QuickTestCaps/7.4/CAPS/training/DARWIN64/ESP/udunits/udunits2-common.xml", line 1571, overrides prefixed-unit "3.6e-09 second"
Definition of "nt" in "/Users/jenkins/workspace/ESP_QuickTestCaps/7.4/CAPS/training/DARWIN64/ESP/udunits/udunits2-common.xml", line 1578, overrides prefixed-unit "1e-06 kilogram"
--> enter ocsmCheck()
--> checks passed
--> enter ocsmSave(filename=capsTmp.cpc)
--> enter ocsmCheck()
--> checks passed
Analysis directory does not currently exist - it will be made automatically
CAPS Info: No symbol for aimDiscr in aflr4AIM
CAPS Info: No symbol for aimFreeDiscr in aflr4AIM
CAPS Info: No symbol for aimLocateElement in aflr4AIM
CAPS Info: No symbol for aimUsesDataSet in aflr4AIM
CAPS Info: No symbol for aimCheck in aflr4AIM
CAPS Info: No symbol for aimTransfer in aflr4AIM
CAPS Info: No symbol for aimInterpolation in aflr4AIM
CAPS Info: No symbol for aimInterpolateBar in aflr4AIM
CAPS Info: No symbol for aimIntegration in aflr4AIM
CAPS Info: No symbol for aimIntegrateBar in aflr4AIM
CAPS Info: No symbol for aimSensitivity in aflr4AIM
Analysis directory does not currently exist - it will be made automatically
CAPS Info: No symbol for aimDiscr in aflr3AIM
CAPS Info: No symbol for aimFreeDiscr in aflr3AIM
CAPS Info: No symbol for aimLocateElement in aflr3AIM
CAPS Info: No symbol for aimUsesDataSet in aflr3AIM
CAPS Info: No symbol for aimCheck in aflr3AIM
CAPS Info: No symbol for aimTransfer in aflr3AIM
CAPS Info: No symbol for aimInterpolation in aflr3AIM
CAPS Info: No symbol for aimInterpolateBar in aflr3AIM
CAPS Info: No symbol for aimIntegration in aflr3AIM
CAPS Info: No symbol for aimIntegrateBar in aflr3AIM
CAPS Info: No symbol for aimSensitivity in aflr3AIM
Analysis directory does not currently exist - it will be made automatically
CAPS Info: No symbol for aimExecute in su2AIM
CAPS Info: No symbol for aimCheck in su2AIM
CAPS Info: No symbol for aimData in su2AIM
CAPS Info: No symbol for aimSensitivity in su2AIM
Analysis directory does not currently exist - it will be made automatically
CAPS Info: No symbol for aimDiscr in egadsTessAIM
CAPS Info: No symbol for aimFreeDiscr in egadsTessAIM
CAPS Info: No symbol for aimLocateElement in egadsTessAIM
CAPS Info: No symbol for aimUsesDataSet in egadsTessAIM
CAPS Info: No symbol for aimCheck in egadsTessAIM
CAPS Info: No symbol for aimTransfer in egadsTessAIM
CAPS Info: No symbol for aimInterpolation in egadsTessAIM
CAPS Info: No symbol for aimInterpolateBar in egadsTessAIM
CAPS Info: No symbol for aimIntegration in egadsTessAIM
CAPS Info: No symbol for aimIntegrateBar in egadsTessAIM
CAPS Info: No symbol for aimSensitivity in egadsTessAIM
Analysis directory does not currently exist - it will be made automatically
CAPS Info: No symbol for aimExecute in astrosAIM
CAPS Info: No symbol for aimCheck in astrosAIM
CAPS Info: No symbol for aimData in astrosAIM
CAPS Info: No symbol for aimSensitivity in astrosAIM
--> enter ocsmBuild(buildTo=0)
--> enter ocsmCheck()
--> checks passed
Interim EGADS version 1.19 (with OpenCASCADE 7.4.1)
executing [ 1] udprim: $/capsHeader (scripted code)
[ 2] interface: . ALL 0.00000
executing [ 3] set: makeFuseOml 0
makeFuseOml = 0.00000 0.00000
executing [ 4] set: makeFuseWaffle 0
makeFuseWaffle = 0.00000 0.00000
executing [ 5] set: makeFuseCmass 0
makeFuseCmass = 0.00000 0.00000
executing [ 6] set: makeWingOml 0
makeWingOml = 0.00000 0.00000
executing [ 7] set: makeWingHinge 0
makeWingHinge = 0.00000 0.00000
executing [ 8] set: makeWingWaffle 0
makeWingWaffle = 0.00000 0.00000
executing [ 9] set: makeWingCmass 0
makeWingCmass = 0.00000 0.00000
executing [ 10] set: makeHtailOml 0
makeHtailOml = 0.00000 0.00000
executing [ 11] set: makeHtailHinge 0
makeHtailHinge = 0.00000 0.00000
executing [ 12] set: makeHtailWaffle 0
makeHtailWaffle = 0.00000 0.00000
executing [ 13] set: makeHtailCmass 0
makeHtailCmass = 0.00000 0.00000
executing [ 14] set: makeVtailOml 0
makeVtailOml = 0.00000 0.00000
executing [ 15] set: makeVtailHinge 0
makeVtailHinge = 0.00000 0.00000
executing [ 16] set: makeVtailWaffle 0
makeVtailWaffle = 0.00000 0.00000
executing [ 17] set: makeVtailCmass 0
makeVtailCmass = 0.00000 0.00000
executing [ 18] set: makePylonOml 0
makePylonOml = 0.00000 0.00000
executing [ 19] set: makePodOml 0
makePodOml = 0.00000 0.00000
executing [ 20] set: SHARP_TE 0
SHARP_TE = 0.00000 0.00000
executing [ 21] ifthen: 0.00000 EQ 1.00000 and ...
executing [ 24] ifthen: 0.00000 NE 0.00000 and ...
executing [ 40] ifthen: 0.00000 EQ 1.00000 and ...
executing [ 43] ifthen: 0.00000 NE 0.00000 and ...
executing [ 51] ifthen: 0.00000 EQ 1.00000 and ...
executing [ 54] ifthen: 1.00000 NE 0.00000 and 0.00000 eq 0.00000
executing [ 55] set: makeFuseOml 1
makeFuseOml = 1.00000 0.00000
executing [ 56] set: makeWingOml 1
makeWingOml = 1.00000 0.00000
executing [ 57] set: makeWingHinge 1
makeWingHinge = 1.00000 0.00000
executing [ 58] set: makeHtailOml 1
makeHtailOml = 1.00000 0.00000
executing [ 59] set: makeHtailHinge 1
makeHtailHinge = 1.00000 0.00000
executing [ 60] set: makeVtailOml 1
makeVtailOml = 1.00000 0.00000
executing [ 61] set: makeVtailHinge 1
makeVtailHinge = 1.00000 0.00000
executing [ 62] set: makePodOml 1
makePodOml = 1.00000 0.00000
executing [ 63] set: SHARP_TE 1
SHARP_TE = 1.00000 0.00000
executing [ 65] ifthen: 0.00000 EQ 1.00000 and ...
executing [ 68] ifthen: 0.00000 NE 0.00000 and ...
executing [ 79] ifthen: 0.00000 EQ 1.00000 and ...
executing [ 82] ifthen: 0.00000 EQ 1.00000 and ...
executing [ 85] ifthen: 0.00000 EQ 1.00000 and ...
executing [ 88] ifthen: 1.00000 NE 0.00000 OR ...
executing [ 89] set: makeWingOml 1
makeWingOml = 1.00000 0.00000
executing [ 90] set: makeWingWaffle 1
makeWingWaffle = 1.00000 0.00000
executing [ 92] ifthen: 0.00000 EQ 1.00000 and ...
executing [ 95] ifthen: 0.00000 NE 0.00000 and ...
executing [ 101] ifthen: 1.00000 EQ 1.00000 and 0.00000 eq 0.00000
executing [ 102] set: COMP:Fuse 0
COMP:Fuse = 0.00000 0.00000
executing [ 104] ifthen: 0.00000 EQ 1.00000 and ...
executing [ 107] ifthen: 1.00000 EQ 1.00000 and 0.00000 eq 0.00000
executing [ 108] set: COMP:Htail 0
COMP:Htail = 0.00000 0.00000
executing [ 110] ifthen: 1.00000 EQ 1.00000 and 0.00000 eq 0.00000
executing [ 111] set: COMP:Vtail 0
COMP:Vtail = 0.00000 0.00000
executing [ 113] ifthen: 1.00000 EQ 1.00000 and 0.00000 eq 0.00000
executing [ 114] set: COMP:Pylon 0
COMP:Pylon = 0.00000 0.00000
executing [ 116] ifthen: 1.00000 EQ 1.00000 and 0.00000 eq 0.00000
executing [ 117] set: COMP:Pod 0
COMP:Pod = 0.00000 0.00000
executing [ 119] ifthen: 1.00000 EQ 1.00000 and 0.00000 eq 0.00000
executing [ 120] set: COMP:Control 0
COMP:Control = 0.00000 0.00000
executing [ 122] ifthen: 0.00000 EQ 0.00000 and 0.00000 eq 0.00000
executing [ 123] set: makeFuseOml 0
makeFuseOml = 0.00000 0.00000
executing [ 124] set: makeFuseWaffle 0
makeFuseWaffle = 0.00000 0.00000
executing [ 125] set: makeFuseCmass 0
makeFuseCmass = 0.00000 0.00000
executing [ 127] ifthen: 1.00000 EQ 0.00000 and ...
executing [ 133] ifthen: 0.00000 EQ 0.00000 and 0.00000 eq 0.00000
executing [ 134] set: makeHtailOml 0
makeHtailOml = 0.00000 0.00000
executing [ 135] set: makeHtailHinge 0
makeHtailHinge = 0.00000 0.00000
executing [ 136] set: makeHtailWaffle 0
makeHtailWaffle = 0.00000 0.00000
executing [ 137] set: makeHtailCmass 0
makeHtailCmass = 0.00000 0.00000
executing [ 139] ifthen: 0.00000 EQ 0.00000 and 0.00000 eq 0.00000
executing [ 140] set: makeVtailOml 0
makeVtailOml = 0.00000 0.00000
executing [ 141] set: makeVtailHinge 0
makeVtailHinge = 0.00000 0.00000
executing [ 142] set: makeVtailWaffle 0
makeVtailWaffle = 0.00000 0.00000
executing [ 143] set: makeVtailCmass 0
makeVtailCmass = 0.00000 0.00000
executing [ 145] ifthen: 0.00000 EQ 0.00000 and 0.00000 eq 0.00000
executing [ 146] set: makePylonOml 0
makePylonOml = 0.00000 0.00000
executing [ 148] ifthen: 0.00000 EQ 0.00000 and 0.00000 eq 0.00000
executing [ 149] set: makePodOml 0
makePodOml = 0.00000 0.00000
executing [ 151] ifthen: 0.00000 EQ 0.00000 and 0.00000 eq 0.00000
executing [ 152] set: makeWingHinge 0
makeWingHinge = 0.00000 0.00000
executing [ 153] set: makeHtailHinge 0
makeHtailHinge = 0.00000 0.00000
executing [ 154] set: makeVtailHinge 0
makeVtailHinge = 0.00000 0.00000
executing [ 156] end:
executing [ 157] set: wing:span sqrt(wing:aspect*wing:area)
wing:span = 7.74597 0.00000
executing [ 158] set: wing:chordr 2*wing:area/wing:span/(1+wing:taper)
wing:chordr = 1.61374 0.00000
executing [ 159] set: wing:chordt wing:chordr*wing:taper
wing:chordt = 0.96825 0.00000
executing [ 160] set: wing:ytip -wing:span/2
wing:ytip = -3.87298 0.00000
executing [ 161] set: wing:xtip -wing:ytip*tand(wing:sweep)
wing:xtip = 1.40965 0.00000
executing [ 162] set: wing:ztip -wing:ytip*tand(wing:dihedral)
wing:ztip = 0.27083 0.00000
executing [ 163] set: wing:mac sqrt(wing:area/wing:aspect)
wing:mac = 1.29099 0.00000
executing [ 164] ifthen: 1.00000 EQ 1.00000 and 0.00000 eq 0.00000
executing [ 165] mark:
Mark created
executing [ 166] udprim: naca thickness 0.12000 camber 0.06000 sharpte 1.00000 (compiled code)
Body 1 created (toler= 1.0000e-07, nnode= 2, nedge= 2, nface= 1)
executing [ 167] scale: 1.61374 0.00000 0.00000 0.00000
Body 2 created (toler= 1.6137e-07, nnode= 2, nedge= 2, nface= 1)
executing [ 168] rotatex: 90.00000 0.00000 0.00000
Body 3 created (toler= 1.6137e-07, nnode= 2, nedge= 2, nface= 1)
executing [ 169] udprim: naca thickness 0.16000 camber 0.02000 sharpte 1.00000 (compiled code)
Body 4 created (toler= 1.0000e-07, nnode= 2, nedge= 2, nface= 1)
executing [ 170] scale: 0.96825 0.00000 0.00000 0.00000
Body 5 created (toler= 1.0000e-07, nnode= 2, nedge= 2, nface= 1)
executing [ 171] rotatex: 90.00000 0.00000 0.00000
Body 6 created (toler= 1.0000e-07, nnode= 2, nedge= 2, nface= 1)
executing [ 172] rotatey: -5.00000 0.00000 0.00000
Body 7 created (toler= 1.0000e-07, nnode= 2, nedge= 2, nface= 1)
executing [ 173] translate: 1.40965 -3.87298 0.27083
Body 8 created (toler= 1.0000e-07, nnode= 2, nedge= 2, nface= 1)
executing [ 174] rule: 0.00000 0.00000
ruling 2 Xsects with 2 Strips each...
Body 9 created (toler= 1.0000e-07, nnode= 4, nedge= 6, nface= 4)
executing [ 175] set: ruledBody @nbody
ruledBody = 9.00000 0.00000
executing [ 176] select: face 9 1
putting Branch Attributes on Face 3
executing [ 177] select: face 9 2
putting Branch Attributes on Face 4
executing [ 178] select: face 9 3
putting Branch Attributes on Face 1
executing [ 179] select: face 9 4
putting Branch Attributes on Face 2
executing [ 180] select: edge 9 3 9 4 1
putting Branch Attributes on Edge 3
executing [ 181] ifthen: 1.00000 EQ 0.00000 and ...
executing [ 183] else:
executing [ 184] select: edge 9 3 9 4 2
putting Branch Attributes on Edge 1
executing [ 186] store: LeftWing 0.00000 1.00000
Body 9 stored
executing [ 187] restore: LeftWing 0.00000
Body 10 restored (toler= 1.0000e-07, nnode= 4, nedge= 6, nface= 4)
executing [ 188] select: face tagType tip * * * *
putting Branch Attributes on Face 4
executing [ 189] select: edge tagType leadingEdge * * * *
executing [ 190] ifthen: 3.00000 GT 0.00000 and 0.00000 eq 0.00000
executing [ 191] select: edge tagType leadingEdge * * * *
putting Branch Attributes on Edge 3
executing [ 193] select: edge tagType trailingEdge * * * *
executing [ 194] ifthen: 1.00000 GT 0.00000 and 0.00000 eq 0.00000
executing [ 195] select: edge tagType trailingEdge * * * *
putting Branch Attributes on Edge 1
executing [ 197] catbeg: $edge_not_found
executing [ 199] mirror: 0.00000 1.00000 0.00000 0.00000
Body 11 created (toler= 1.0000e-07, nnode= 4, nedge= 6, nface= 4)
executing [ 200] join: 0.00000 0.00000
Body 12 created (toler= 1.0000e-07, nnode= 6, nedge= 10, nface= 6)
executing [ 201] select: edge 9 3 9 3 1
putting Branch Attributes on Edge 2
executing [ 202] select: edge 9 4 9 4 1
putting Branch Attributes on Edge 5
executing [ 203] store: WingOml 0.00000 0.00000
Body 12 stored
executing [ 205] ifthen: 1.00000 EQ 1.00000 and 0.00000 eq 0.00000
executing [ 206] restore: WingOml 0.00000
Body 13 restored (toler= 1.0000e-07, nnode= 6, nedge= 10, nface= 6)
executing [ 207] set: xmin @xmin-0.1
xmin = -0.10102 0.00000
executing [ 208] set: xmax @xmax+0.1
xmax = 2.47421 0.00000
executing [ 209] set: ymin 0
ymin = 0.00000 0.00000
executing [ 210] set: ymax @ymax+0.1
ymax = 3.97298 0.00000
executing [ 211] set: zmin @zmin-0.1
zmin = -0.13316 0.00000
executing [ 212] set: zmax @zmax+0.1
zmax = 0.49990 0.00000
executing [ 213] store: . 0.00000 0.00000
Body 13 removed from stack
executing [ 214] udparg: waffle depth 3.00000
Body 14 created (NULL Body)
executing [ 215] udparg: waffle depth 0.20000
Body 15 created (NULL Body)
executing [ 216] udparg: waffle depth 0.70000
Body 16 created (NULL Body)
executing [ 217] udprim: waffle depth 0.63306 filename tmp_OpenCSM_00/00 (compiled code)
processing:
processing: # construction lines for spars
processing: CPOINT A AT 0+wing:spar1*wing:chordr 0
processing: CPOINT B AT wing:xtip+wing:spar1*wing:chordt -wing:ytip
processing: CPOINT C AT 0+wing:spar2*wing:chordr 0
processing: CPOINT D AT wing:xtip+wing:spar2*wing:chordt -wing:ytip
processing:
processing: CLINE AB A B
processing: CLINE CD C D
processing:
processing: # rite spars
processing: POINT E ON AB YLOC ymin
processing: POINT F ON AB YLOC ymax
processing: LINE EF E F tagComp=riteWing tagType=spar tagIndex=1
processing:
processing: POINT G ON CD YLOC ymin
processing: POINT H ON CD YLOC ymax
processing: LINE GH G H tagComp=riteWing tagType=spar tagIndex=2
processing:
processing: # rite ribs
processing: PATBEG irib wing:nrib
processing: CPOINT I AT xmin -wing:ytip*irib/(wing:nrib+1)
processing: CPOINT J AT xmax y@I
processing: LINE . I J tagComp=riteWing tagType=rib tagIndex=!val2str(irib,0)
processing: PATEND
processing: CPOINT I AT xmin -wing:ytip*irib/(wing:nrib+1)
processing: CPOINT J AT xmax y@I
processing: LINE . I J tagComp=riteWing tagType=rib tagIndex=!val2str(irib,0)
processing: PATEND
processing: CPOINT I AT xmin -wing:ytip*irib/(wing:nrib+1)
processing: CPOINT J AT xmax y@I
processing: LINE . I J tagComp=riteWing tagType=rib tagIndex=!val2str(irib,0)
processing: PATEND
processing:
processing: # root rib
processing: CPOINT I AT xmin 0
processing: CPOINT J AT xmax y@I
processing: LINE . I J tagComp=rootWing tagType=rib tagIndex=0
processing:
processing: # left spars
processing: POINT E AT x@E -y@E
processing: POINT F AT x@F -y@F
processing: LINE FE F E tagComp=leftWing tagType=spar tagIndex=1
processing:
processing: POINT G AT x@G -y@G
processing: POINT H AT x@H -y@H
processing: LINE HG H G tagComp=leftWing tagType=spar tagIndex=2
processing:
processing: # left ribs
processing: PATBEG irib wing:nrib
processing: CPOINT I AT xmin wing:ytip*irib/(wing:nrib+1)
processing: CPOINT J AT xmax y@I
processing: LINE . I J tagComp=leftWing tagType=rib tagIndex=!val2str(irib,0)
processing: PATEND
processing: CPOINT I AT xmin wing:ytip*irib/(wing:nrib+1)
processing: CPOINT J AT xmax y@I
processing: LINE . I J tagComp=leftWing tagType=rib tagIndex=!val2str(irib,0)
processing: PATEND
processing: CPOINT I AT xmin wing:ytip*irib/(wing:nrib+1)
processing: CPOINT J AT xmax y@I
processing: LINE . I J tagComp=leftWing tagType=rib tagIndex=!val2str(irib,0)
processing: PATEND
Body 17 created (toler= 1.0000e-07, nnode= 64, nedge= 106, nface= 37)
executing [ 218] translate: 0.00000 0.00000 -0.13316
Body 18 created (toler= 1.0000e-07, nnode= 64, nedge= 106, nface= 37)
executing [ 219] store: WingWaffle 0.00000 0.00000
Body 18 stored
executing [ 221] udprim: $/capsViews (scripted code)
[ 222] interface: . ALL 0.00000
executing [ 223] ifthen: 0.00000 NE 0.00000 and ...
executing [ 268] ifthen: 0.00000 NE 0.00000 and ...
executing [ 409] ifthen: 1.00000 NE 0.00000 and 0.00000 eq 0.00000
executing [ 410] udprim: $/viewCFDInviscid (scripted code)
[ 411] interface: . ALL 0.00000
executing [ 412] set: cfdAIMs $tetgenAIM;aflr3AIM;aflr4AIM;pointwiseAIM;su2AIM;fun3dAIM
cfdAIMs = $tetgenAIM;aflr3AIM;aflr4AIM;pointwiseAIM;su2AIM;fun3dAIM
executing [ 413] set: AFLR4_Cmp_Fuse 1
AFLR4_Cmp_Fuse = 1.00000 0.00000
executing [ 414] set: AFLR4_Cmp_Wing 2
AFLR4_Cmp_Wing = 2.00000 0.00000
executing [ 415] set: AFLR4_Cmp_Htail 3
AFLR4_Cmp_Htail = 3.00000 0.00000
executing [ 416] set: AFLR4_Cmp_Vtail 4
AFLR4_Cmp_Vtail = 4.00000 0.00000
executing [ 417] set: AFLR4_Cmp_Pod 5
AFLR4_Cmp_Pod = 5.00000 0.00000
executing [ 418] set: AFLR4_Cmp_Farfield 6
AFLR4_Cmp_Farfield = 6.00000 0.00000
executing [ 419] ifthen: 1.00000 EQ 1.00000 and 0.00000 eq 0.00000
executing [ 420] set: MESH:SIZE 1
MESH:SIZE = 1.00000 0.00000
executing [ 422] set: ffxmin 1e3
ffxmin = 1000.00000 0.00000
executing [ 423] set: ffxmax -1e3
ffxmax = -1000.00000 0.00000
executing [ 424] set: ffymin 1e3
ffymin = 1000.00000 0.00000
executing [ 425] set: ffymax -1e3
ffymax = -1000.00000 0.00000
executing [ 426] set: ffzmin 1e3
ffzmin = 1000.00000 0.00000
executing [ 427] set: ffzmax -1e3
ffzmax = -1000.00000 0.00000
executing [ 428] ifthen: 0.00000 EQ 1.00000 and ...
executing [ 448] ifthen: 1.00000 EQ 1.00000 and 0.00000 eq 0.00000
executing [ 449] restore: WingOml 0.00000
Body 19 restored (toler= 1.0000e-07, nnode= 6, nedge= 10, nface= 6)
executing [ 450] store: WingOml_CFD 0.00000 1.00000
Body 19 stored
executing [ 451] set: xmax @xmax
xmax = 2.37421 0.00000
executing [ 452] set: zmin @zmin
zmin = -0.03316 0.00000
executing [ 453] set: zmax @zmax
zmax = 0.39990 0.00000
executing [ 454] udprim: $/ffbox (scripted code)
[ 455] interface: . ALL 0.00000
executing [ 456] set: ffxmin min(ffxmin,@xmin)
ffxmin = -0.00102 0.00000
executing [ 457] set: ffxmax max(ffxmax,@xmax)
ffxmax = 2.37421 0.00000
executing [ 458] set: ffymin min(ffymin,@ymin)
ffymin = -3.87298 0.00000
executing [ 459] set: ffymax max(ffymax,@ymax)
ffymax = 3.87298 0.00000
executing [ 460] set: ffzmin min(ffzmin,@zmin)
ffzmin = -0.03316 0.00000
executing [ 461] set: ffzmax max(ffzmax,@zmax)
ffzmax = 0.39990 0.00000
executing [ 462] end:
executing [ 463] udprim: editAttr filename tmp_OpenCSM_00/01 (compiled code)
processing: FACE HAS tagType=upper
processing: SET capsBound=upperWing
processing:
processing: FACE HAS tagType=lower
processing: SET capsBound=lowerWing
processing:
processing: FACE HAS tagType=tip tagIndex=1
processing: SET capsBound=leftTip
processing:
processing: FACE HAS tagType=tip tagIndex=2
processing: SET capsBound=riteTip
Body 20 created (toler= 1.0000e-07, nnode= 6, nedge= 10, nface= 6)
executing [ 464] ifthen: 0.00000 EQ 1.00000 and ...
executing [ 566] select: face
putting Branch Attributes on Face 1
putting Branch Attributes on Face 2
putting Branch Attributes on Face 3
putting Branch Attributes on Face 4
putting Branch Attributes on Face 5
putting Branch Attributes on Face 6
executing [ 567] ifthen: 0.00000 EQ 1.00000 and ...
executing [ 569] else:
executing [ 570] store: WingOml_CFD 0.00000 0.00000
WARNING:: storage WingOml_CFD (0) is being overwritten
Body 20 stored
executing [ 573] ifthen: 0.00000 EQ 1.00000 and ...
executing [ 697] ifthen: 0.00000 EQ 1.00000 and ...
executing [ 821] ifthen: 0.00000 EQ 1.00000 and ...
executing [ 824] ifthen: 0.00000 EQ 1.00000 and ...
executing [ 827] else:
executing [ 828] ifthen: 1.00000 EQ 1.00000 and 0.00000 eq 0.00000
executing [ 829] restore: WingOml_CFD 0.00000
Body 21 restored (toler= 1.0000e-07, nnode= 6, nedge= 10, nface= 6)
executing [ 830] select: body
putting Branch Attributes on Body
executing [ 832] ifthen: 0.00000 EQ 1.00000 and ...
executing [ 836] ifthen: 0.00000 EQ 1.00000 and ...
executing [ 841] ifthen: 0.00000 EQ 1.00000 and ...
executing [ 847] set: size 20*max(ffxmax-ffxmin,ffymax-ffymin)
size = 154.91934 0.00000
executing [ 848] box: -76.27307 -77.45967 -77.27630 154.91934 154.91934 154.91934
Body 22 created (toler= 1.0000e-07, nnode= 8, nedge= 12, nface= 6)
executing [ 849] select: body
putting Branch Attributes on Body
executing [ 850] end:
executing [ 852] ifthen: 0.00000 NE 0.00000 and ...
executing [1290] ifthen: 1.00000 NE 0.00000 OR ...
executing [1291] udprim: $/viewStructure (scripted code)
[1292] interface: . ALL 0.00000
executing [1293] set: structAIMs $nastranAIM;astrosAIM;mystranAIM;egadsTessAIM
structAIMs = $nastranAIM;astrosAIM;mystranAIM;egadsTessAIM
executing [1294] ifthen: 1.00000 EQ 1.00000 and 0.00000 eq 0.00000
executing [1295] restore: WingOml 0.00000
Body 23 restored (toler= 1.0000e-07, nnode= 6, nedge= 10, nface= 6)
executing [1296] restore: WingWaffle 0.00000
Body 24 restored (toler= 1.0000e-07, nnode= 64, nedge= 106, nface= 37)
executing [1297] intersect: none 1.00000 0.0000e+00
Body 25 created (toler= 5.0000e-06, nnode= 50, nedge= 92, nface= 37)
executing [1298] restore: WingOml 0.00000
Body 26 restored (toler= 1.0000e-07, nnode= 6, nedge= 10, nface= 6)
executing [1299] restore: WingWaffle 0.00000
Body 27 restored (toler= 1.0000e-07, nnode= 64, nedge= 106, nface= 37)
executing [1300] subtract: none 1.00000 0.0000e+00
Body 28 created (toler= 1.0749e-06, nnode= 54, nedge= 106, nface= 54)
executing [1301] extract: 0
Body 29 created (toler= 1.0749e-06, nnode= 54, nedge= 106, nface= 54)
executing [1302] union: 0.00000 0 0.0000e+00
Body 30 created (toler= 5.0000e-06, nnode= 54, nedge= 120, nface= 91)
executing [1303] ifthen: 0.00000 EQ 1.00000 and ...
executing [1306] else:
executing [1307] udprim: editAttr filename tmp_OpenCSM_00/05 (compiled code)
processing: FACE HAS tagComp=leftWing
processing: SET capsGroup=leftWingSkin
processing:
processing: FACE HAS tagComp=riteWing
processing: SET capsGroup=riteWingSkin
processing:
processing: FACE HAS tagType=tip
processing: SET capsGroup=wingRib
processing:
processing: FACE HAS tagType=trailingEdge
processing: SET capsGroup=wingTE
processing:
processing: FACE HAS tagType=rib
processing: SET capsGroup=wingRib
processing:
processing: FACE HAS tagType=spar tagIndex=1
processing: SET capsGroup=wingSpar1
processing: SET capsMesh=wingSpar1
processing:
processing: FACE HAS tagType=spar tagIndex=2
processing: SET capsGroup=wingSpar2
processing: SET capsMesh=wingSpar2
WARNING:: toler = 5.0000e-06 for UDPRIM
Body 31 created (toler= 5.0000e-06, nnode= 54, nedge= 120, nface= 91)
executing [1309] udprim: editAttr filename tmp_OpenCSM_00/06 (compiled code)
processing: FACE HAS tagType=upper
processing: SET capsBound=upperWing
processing:
processing: FACE HAS tagType=lower
processing: SET capsBound=lowerWing
processing:
processing: FACE HAS tagType=tip tagIndex=1
processing: SET capsBound=leftTip
processing:
processing: FACE HAS tagType=tip tagIndex=2
processing: SET capsBound=riteTip
WARNING:: toler = 5.0000e-06 for UDPRIM
Body 32 created (toler= 5.0000e-06, nnode= 54, nedge= 120, nface= 91)
executing [1310] udprim: editAttr filename tmp_OpenCSM_00/07 (compiled code)
processing: NODE ADJ2FACE tagComp=leftWing tagType=tip
processing: AND ADJ2FACE tagType=lower
processing: AND ADJ2FACE tagType=spar tagIndex=1
processing: SET capsLoad=leftPointLoad
processing:
processing: NODE ADJ2FACE tagComp=riteWing tagType=tip
processing: AND ADJ2FACE tagType=lower
processing: AND ADJ2FACE tagType=spar tagIndex=1
processing: SET capsLoad=ritePointLoad
WARNING:: toler = 5.0000e-06 for UDPRIM
Body 33 created (toler= 5.0000e-06, nnode= 54, nedge= 120, nface= 91)
executing [1311] select: edge tagType leadingEdge * * * *
executing [1312] dimension: leadingEdges 1.00000 8.00000
executing [1313] set: leadingEdges @sellist
leadingEdges[1,1] = 8.00000 0.00000
leadingEdges[1,2] = 31.00000 0.00000
leadingEdges[1,3] = 33.00000 0.00000
leadingEdges[1,4] = 59.00000 0.00000
leadingEdges[1,5] = 61.00000 0.00000
leadingEdges[1,6] = 87.00000 0.00000
leadingEdges[1,7] = 89.00000 0.00000
leadingEdges[1,8] = 110.00000 0.00000
executing [1314] patbeg: i 8.00000
pattern counter: i = 1
executing [1315] select: edge 8
putting Branch Attributes on Edge 8
executing [1316] patend:
pattern counter: i = 2
executing [1315] select: edge 31
putting Branch Attributes on Edge 31
executing [1316] patend:
pattern counter: i = 3
executing [1315] select: edge 33
putting Branch Attributes on Edge 33
executing [1316] patend:
pattern counter: i = 4
executing [1315] select: edge 59
putting Branch Attributes on Edge 59
executing [1316] patend:
pattern counter: i = 5
executing [1315] select: edge 61
putting Branch Attributes on Edge 61
executing [1316] patend:
pattern counter: i = 6
executing [1315] select: edge 87
putting Branch Attributes on Edge 87
executing [1316] patend:
pattern counter: i = 7
executing [1315] select: edge 89
putting Branch Attributes on Edge 89
executing [1316] patend:
pattern counter: i = 8
executing [1315] select: edge 110
putting Branch Attributes on Edge 110
executing [1316] patend:
executing [1317] udprim: editAttr filename tmp_OpenCSM_00/08 (compiled code)
processing: FACE ADJ2EDGE tagComp=leftWing
processing: SET tagTemp=leadingEdgeFace
WARNING:: toler = 5.0000e-06 for UDPRIM
Body 34 created (toler= 5.0000e-06, nnode= 54, nedge= 120, nface= 91)
executing [1318] udprim: editAttr filename tmp_OpenCSM_00/09 (compiled code)
processing: EDGE ADJ2FACE tagTemp=leadingEdgeFace
processing: AND ADJ2FACE tagComp=rootWing
processing: SET capsMesh=rootLeadingEdge
WARNING:: toler = 5.0000e-06 for UDPRIM
Body 35 created (toler= 5.0000e-06, nnode= 54, nedge= 120, nface= 91)
executing [1319] ifthen: 1.00000 EQ 1.00000 and 0.00000 eq 0.00000
executing [1320] udprim: editAttr filename tmp_OpenCSM_00/10 (compiled code)
processing: FACE HAS tagComp=rootWing
processing: SET capsConstraint=rootConstraint
processing:
processing: EDGE ADJ2FACE tagComp=rootWing
processing: SET capsConstraint=rootConstraint
processing:
processing: NODE ADJ2FACE tagComp=rootWing
processing: SET capsConstraint=rootConstraint
WARNING:: toler = 5.0000e-06 for UDPRIM
Body 36 created (toler= 5.0000e-06, nnode= 54, nedge= 120, nface= 91)
executing [1322] ifthen: 0.00000 EQ 1.00000 and ...
executing [1325] udprim: editAttr filename tmp_OpenCSM_00/12 (compiled code)
processing: FACE HAS tagComp=leftWing tagType=upper
processing: AND ADJ2EDGE tagType=leadingEdge
processing: AND ADJ2FACE tagComp=riteWing
processing: SET tagCsys=leftWing
processing:
processing: FACE HAS tagComp=riteWing tagType=upper
processing: AND ADJ2EDGE tagType=leadingEdge
processing: AND ADJ2FACE tagComp=leftWing
processing: SET tagCsys=riteWing
WARNING:: toler = 5.0000e-06 for UDPRIM
Body 37 created (toler= 5.0000e-06, nnode= 54, nedge= 120, nface= 91)
executing [1326] select: face tagCsys leftWing * * * *
executing [1327] set: leftWingSkinCsys @sellist
leftWingSkinCsys = 27.00000 0.00000
executing [1328] select: face tagCsys riteWing * * * *
executing [1329] set: riteWingSkinCsys @sellist
riteWingSkinCsys = 8.00000 0.00000
executing [1330] store: WingStruct 0.00000 0.00000
Body 37 stored
executing [1331] restore: WingStruct 0.00000
Body 38 restored (toler= 5.0000e-06, nnode= 54, nedge= 120, nface= 91)
executing [1332] store: WingStruct 0.00000 0.00000
WARNING:: storage WingStruct (0) is being overwritten
Body 38 stored
executing [1334] restore: WingStruct 0.00000
Body 39 restored (toler= 5.0000e-06, nnode= 54, nedge= 120, nface= 91)
executing [1335] select: body
putting Branch Attributes on Body
executing [1336] ifthen: 0.00000 EQ 1.00000 and ...
executing [1339] end:
executing [1341] ifthen: 0.00000 NE 0.00000 and ...
executing [1378] end:
finalizing:
==> Profile information
Branch type ncall time (sec) pct
dimension 1 0.000 0.0
box 1 0.001 0.0
udprim 16 0.372 0.4
restore 10 0.035 0.0
rule 1 0.045 0.1
intersect 1 17.581 20.5
subtract 1 18.543 21.7
union 1 48.177 56.3
join 1 0.078 0.1
extract 1 0.644 0.8
translate 2 0.013 0.0
rotatex 2 0.002 0.0
rotatey 1 0.001 0.0
scale 2 0.002 0.0
mirror 1 0.023 0.0
interface 5 0.000 0.0
end 5 0.000 0.0
set 93 0.002 0.0
udparg 3 0.000 0.0
select 28 0.080 0.1
store 8 0.000 0.0
patbeg 1 0.000 0.0
patend 8 0.000 0.0
ifthen 57 0.001 0.0
else 4 0.000 0.0
endif 57 0.000 0.0
catbeg 1 0.000 0.0
mark 1 0.000 0.0
Total 313 85.602
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 2
Name = Wing, index = 1
Name = Farfield, index = 2
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 2
Name = Wing, index = 1
Name = Farfield, index = 2
Getting mesh sizing parameters
Mesh sizing name - Wing
Mesh sizing name - Farfield
Done getting mesh sizing parameters
AFLR2 : ---------------------------------------
AFLR2 : AFLR2 LIBRARY
AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR2 : TRIA/QUAD GRID GENERATOR
AFLR2 : Version Number 9.13.13
AFLR2 : Version Date 10/10/20 @ 10:50PM
AFLR2 : Compile OS Darwin 19.6.0 x86_64
AFLR2 : Compile Date 10/10/20 @ 10:50PM
AFLR2 : Copyright 1994-2020, D.L. Marcum
AFLR2 : ---------------------------------------
AFLR4 : ---------------------------------------
AFLR4 : AFLR4 LIBRARY
AFLR4 : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR4 : TRIA/QUAD SURFACE GRID GENERATOR
AFLR4 : Version Number 10.11.10
AFLR4 : Version Date 10/30/20 @ 03:19PM
AFLR4 : Compile OS Darwin 19.6.0 x86_64
AFLR4 : Compile Date 10/30/20 @ 03:19PM
AFLR4 : Copyright 1994-2020, D.L. Marcum
AFLR4 : ---------------------------------------
EGADS : EGADS CAD Geometry Setup
EGADS : Using EGADS Version 1.19
EGADS : Using OpenCASCADE Version ase with OpenCASCADE 7.4.1
EGADS : Model has 2 Bodies
EGADS : Body 0 is a SolidBody
EGADS : Body 0 has 1 BRep Shells
EGADS : Body 0 has 6 BRep Faces
EGADS : Body 0 has 10 BRep Edges
EGADS : Body 0 has 6 BRep Nodes
EGADS : Body 1 is a SolidBody
EGADS : Body 1 has 1 BRep Shells
EGADS : Body 1 has 6 BRep Faces
EGADS : Body 1 has 12 BRep Edges
EGADS : Body 1 has 8 BRep Nodes
AFLR4 : Surface Mesh Spacing Setup
AFLR4 : Max Bounding Box Length = 154.919
AFLR4 : Min Bounding Box Length = 154.919
AFLR4 : Max Ref Bounding Box Length = 7.74597
AFLR4 : Min Ref Bounding Box Length = 0.433058
AFLR4 : Reference Length = 6.45497
AFLR4 : BL Thickness = 0
AFLR4 : FarField Spacing = 21.0478
AFLR4 : Abs Min Surf Spacing = 0.0161374
AFLR4 : Min Surf Spacing = 0.0322749
AFLR4 : Max Surf Spacing = 0.645497
AFLR4 : Check Grid BCs
AFLR4 : Grid BCs are OK
AFLR4 : Geometry Definition Information
AFLR4 : IER = Isolated Edge Refinement
AFLR4 : ER = Edge Refinement
AFLR4 : Definition Definition Composite Grid BC IER ER Scale
AFLR4 : ID Type ID Type Flag Weight Factor
AFLR4 : 0 glue-only composite - - - - -
AFLR4 : 1 CAD geometry 0 STD w/BL 1 1 1
AFLR4 : 2 CAD geometry 0 STD w/BL 1 1 1
AFLR4 : 3 CAD geometry 0 STD w/BL 1 1 1
AFLR4 : 4 CAD geometry 0 STD w/BL 1 1 1
AFLR4 : 5 CAD geometry 0 STD w/BL 1 1 1
AFLR4 : 6 CAD geometry 0 STD w/BL 1 1 1
AFLR4 : 7 CAD geometry 0 FARFIELD 1 0 1
AFLR4 : 8 CAD geometry 0 FARFIELD 1 0 1
AFLR4 : 9 CAD geometry 0 FARFIELD 1 0 1
AFLR4 : 10 CAD geometry 0 FARFIELD 1 0 1
AFLR4 : 11 CAD geometry 0 FARFIELD 1 0 1
AFLR4 : 12 CAD geometry 0 FARFIELD 1 0 1
AFLR4 : Definition Neighbor Map
AFLR4 : Definition Neighbor-Definitions
AFLR4 : 1 4 2 3
AFLR4 : 2 1 5 3
AFLR4 : 3 1 2
AFLR4 : 4 1 5 6
AFLR4 : 5 2 4 6
AFLR4 : 6 4 5
AFLR4 : 7 9 12 10 11
AFLR4 : 8 9 12 10 11
AFLR4 : 9 7 8 11 12
AFLR4 : 10 7 8 11 12
AFLR4 : 11 7 8 9 10
AFLR4 : 12 7 8 9 10
AFLR4 : Define CAD surface definition 1
AFLR4 : Define CAD surface definition 2
AFLR4 : Define CAD surface definition 3
AFLR4 : Define CAD surface definition 4
AFLR4 : Define CAD surface definition 5
AFLR4 : Define CAD surface definition 6
AFLR4 : Define CAD surface definition 7
AFLR4 : Define CAD surface definition 8
AFLR4 : Define CAD surface definition 9
AFLR4 : Define CAD surface definition 10
AFLR4 : Define CAD surface definition 11
AFLR4 : Define CAD surface definition 12
AFLR4 : Surface Grid Generation
AFLR4 : Generate optimal mesh on surface definition 1
AFLR2 : Nodes, Faces = 1364 2547
AFLR4 : Nodes, Faces = 1007 1833
AFLR4 : Generate optimal mesh on surface definition 2
AFLR2 : Nodes, Faces = 1335 2491
AFLR4 : Nodes, Faces = 952 1725
AFLR4 : Generate optimal mesh on surface definition 3
AFLR2 : Nodes, Faces = 48 65
AFLR4 : Nodes, Faces = 44 57
AFLR4 : Generate optimal mesh on surface definition 4
AFLR2 : Nodes, Faces = 1368 2555
AFLR4 : Nodes, Faces = 1005 1829
AFLR4 : Generate optimal mesh on surface definition 5
AFLR2 : Nodes, Faces = 1330 2481
AFLR4 : Nodes, Faces = 944 1709
AFLR4 : Generate optimal mesh on surface definition 6
AFLR2 : Nodes, Faces = 48 65
AFLR4 : Nodes, Faces = 44 57
AFLR4 : Generate optimal mesh on surface definition 7
AFLR2 : Nodes, Faces = 73 116
AFLR4 : Nodes, Faces = 68 106
AFLR4 : Generate optimal mesh on surface definition 8
AFLR2 : Nodes, Faces = 73 116
AFLR4 : Nodes, Faces = 68 106
AFLR4 : Generate optimal mesh on surface definition 9
AFLR2 : Nodes, Faces = 73 116
AFLR4 : Nodes, Faces = 68 106
AFLR4 : Generate optimal mesh on surface definition 10
AFLR2 : Nodes, Faces = 73 116
AFLR4 : Nodes, Faces = 68 106
AFLR4 : Generate optimal mesh on surface definition 11
AFLR2 : Nodes, Faces = 73 116
AFLR4 : Nodes, Faces = 68 106
AFLR4 : Generate optimal mesh on surface definition 12
AFLR2 : Nodes, Faces = 73 116
AFLR4 : Nodes, Faces = 68 106
DGEOM : Add surface definitions to composite definition 0
DGEOM : Glue composite surface definition 0
DGEOM : Nodes, Faces = 3927 7846
AFLR4 : Curvature BG Surface Grid Generation
AFLR4 : Nodes, Faces = 3927 7846
AFLR4 : Surface Grid Generation
AFLR4 : Generate optimal mesh on surface definition 1
AFLR2 : Nodes, Faces = 3393 6475
AFLR4 : Nodes, Faces = 2440 4569
AFLR4 : Generate optimal mesh on surface definition 2
AFLR2 : Nodes, Faces = 3382 6454
AFLR4 : Nodes, Faces = 2273 4236
AFLR4 : Generate optimal mesh on surface definition 3
AFLR2 : Nodes, Faces = 145 226
AFLR4 : Nodes, Faces = 137 210
AFLR4 : Generate optimal mesh on surface definition 4
AFLR2 : Nodes, Faces = 3394 6477
AFLR4 : Nodes, Faces = 2423 4535
AFLR4 : Generate optimal mesh on surface definition 5
AFLR2 : Nodes, Faces = 3402 6494
AFLR4 : Nodes, Faces = 2288 4266
AFLR4 : Generate optimal mesh on surface definition 6
AFLR2 : Nodes, Faces = 145 226
AFLR4 : Nodes, Faces = 137 210
AFLR4 : Generate optimal mesh on surface definition 7
AFLR2 : Nodes, Faces = 73 116
AFLR4 : Nodes, Faces = 68 106
AFLR4 : Generate optimal mesh on surface definition 8
AFLR2 : Nodes, Faces = 73 116
AFLR4 : Nodes, Faces = 68 106
AFLR4 : Generate optimal mesh on surface definition 9
AFLR2 : Nodes, Faces = 73 116
AFLR4 : Nodes, Faces = 68 106
AFLR4 : Generate optimal mesh on surface definition 10
AFLR2 : Nodes, Faces = 73 116
AFLR4 : Nodes, Faces = 68 106
AFLR4 : Generate optimal mesh on surface definition 11
AFLR2 : Nodes, Faces = 73 116
AFLR4 : Nodes, Faces = 68 106
AFLR4 : Generate optimal mesh on surface definition 12
AFLR2 : Nodes, Faces = 73 116
AFLR4 : Nodes, Faces = 68 106
DGEOM : Add surface definitions to composite definition 0
DGEOM : Glue composite surface definition 0
DGEOM : Nodes, Faces = 9335 18662
OVERALL : CPU Time = 0.272 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 = 0.025 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 = 0.350 seconds
AFLR3 GG : ISOTROPIC VOLUME GRID GENERATION
AFLR3 GG : Nodes, Elements = 9335 28327
AFLR3 GG : Nodes, Elements = 13664 41383
AFLR3 GG : Nodes, Elements = 13664 58327
AFLR3 GG : Nodes, Elements = 13664 53926
AFLR3 GG : Nodes, Elements = 17251 65070
AFLR3 GG : Nodes, Elements = 17251 79156
AFLR3 GG : Nodes, Elements = 17251 74584
AFLR3 GG : Nodes, Elements = 20911 85936
AFLR3 GG : Nodes, Elements = 20911 100204
AFLR3 GG : Nodes, Elements = 20911 96106
AFLR3 GG : Nodes, Elements = 24578 107285
AFLR3 GG : Nodes, Elements = 24578 122135
AFLR3 GG : Nodes, Elements = 24578 118000
AFLR3 GG : Nodes, Elements = 28268 129223
AFLR3 GG : Nodes, Elements = 28268 143781
AFLR3 GG : Nodes, Elements = 28268 139869
AFLR3 GG : Nodes, Elements = 31926 150933
AFLR3 GG : Nodes, Elements = 31926 165332
AFLR3 GG : Nodes, Elements = 31926 161553
AFLR3 GG : Nodes, Elements = 35485 172289
AFLR3 GG : Nodes, Elements = 35485 186302
AFLR3 GG : Nodes, Elements = 35485 182688
AFLR3 GG : Nodes, Elements = 39014 193325
AFLR3 GG : Nodes, Elements = 39014 207191
AFLR3 GG : Nodes, Elements = 39014 203616
AFLR3 GG : Nodes, Elements = 42380 213746
AFLR3 GG : Nodes, Elements = 42380 226774
AFLR3 GG : Nodes, Elements = 42380 223470
AFLR3 GG : Nodes, Elements = 45594 233143
AFLR3 GG : Nodes, Elements = 45594 245701
AFLR3 GG : Nodes, Elements = 45594 242579
AFLR3 GG : Nodes, Elements = 48680 251862
AFLR3 GG : Nodes, Elements = 48680 263885
AFLR3 GG : Nodes, Elements = 48680 260843
AFLR3 GG : Nodes, Elements = 51607 269642
AFLR3 GG : Nodes, Elements = 51607 281129
AFLR3 GG : Nodes, Elements = 51607 278242
AFLR3 GG : Nodes, Elements = 54466 286829
AFLR3 GG : Nodes, Elements = 54466 298009
AFLR3 GG : Nodes, Elements = 54466 295289
AFLR3 GG : Nodes, Elements = 57175 303426
AFLR3 GG : Nodes, Elements = 57175 314032
AFLR3 GG : Nodes, Elements = 57175 311347
AFLR3 GG : Nodes, Elements = 59734 319030
AFLR3 GG : Nodes, Elements = 59734 329059
AFLR3 GG : Nodes, Elements = 59734 326537
AFLR3 GG : Nodes, Elements = 62197 333935
AFLR3 GG : Nodes, Elements = 62197 343560
AFLR3 GG : Nodes, Elements = 62197 341234
AFLR3 GG : Nodes, Elements = 64493 348127
AFLR3 GG : Nodes, Elements = 64493 357104
AFLR3 GG : Nodes, Elements = 64493 354919
AFLR3 GG : Nodes, Elements = 66655 361408
AFLR3 GG : Nodes, Elements = 66655 369771
AFLR3 GG : Nodes, Elements = 66655 367737
AFLR3 GG : Nodes, Elements = 68691 373851
AFLR3 GG : Nodes, Elements = 68691 381683
AFLR3 GG : Nodes, Elements = 68691 379827
AFLR3 GG : Nodes, Elements = 70623 385623
AFLR3 GG : Nodes, Elements = 70623 393122
AFLR3 GG : Nodes, Elements = 70623 391269
AFLR3 GG : Nodes, Elements = 72365 396500
AFLR3 GG : Nodes, Elements = 72365 403287
AFLR3 GG : Nodes, Elements = 72365 401668
AFLR3 GG : Nodes, Elements = 74030 406665
AFLR3 GG : Nodes, Elements = 74030 413119
AFLR3 GG : Nodes, Elements = 74030 411573
AFLR3 GG : Nodes, Elements = 75529 416071
AFLR3 GG : Nodes, Elements = 75529 421907
AFLR3 GG : Nodes, Elements = 75529 420507
AFLR3 GG : Nodes, Elements = 76869 424529
AFLR3 GG : Nodes, Elements = 76869 429740
AFLR3 GG : Nodes, Elements = 76869 428485
AFLR3 GG : Nodes, Elements = 78055 432045
AFLR3 GG : Nodes, Elements = 78055 436697
AFLR3 GG : Nodes, Elements = 78055 435531
AFLR3 GG : Nodes, Elements = 79029 438454
AFLR3 GG : Nodes, Elements = 79029 442292
AFLR3 GG : Nodes, Elements = 79029 441330
AFLR3 GG : Nodes, Elements = 79832 443739
AFLR3 GG : Nodes, Elements = 79832 446926
AFLR3 GG : Nodes, Elements = 79832 446120
AFLR3 GG : Nodes, Elements = 80482 448071
AFLR3 GG : Nodes, Elements = 80482 450702
AFLR3 GG : Nodes, Elements = 80482 449971
AFLR3 GG : Nodes, Elements = 80956 451393
AFLR3 GG : Nodes, Elements = 80956 453377
AFLR3 GG : Nodes, Elements = 80956 452794
AFLR3 GG : Nodes, Elements = 81261 453709
AFLR3 GG : Nodes, Elements = 81261 454931
AFLR3 GG : Nodes, Elements = 81261 454583
AFLR3 GG : Nodes, Elements = 81421 455063
AFLR3 GG : Nodes, Elements = 81421 455738
AFLR3 GG : Nodes, Elements = 81421 455501
AFLR3 GG : Nodes, Elements = 81492 455714
AFLR3 GG : Nodes, Elements = 81492 456042
AFLR3 GG : Nodes, Elements = 81492 455920
AFLR3 GG : Nodes, Elements = 81521 456007
AFLR3 GG : Nodes, Elements = 81521 456151
AFLR3 GG : Nodes, Elements = 81521 456083
AFLR3 GG : Nodes, Elements = 81534 456122
AFLR3 GG : Nodes, Elements = 81534 456170
AFLR3 GG : Nodes, Elements = 81534 456152
AFLR3 GG : Nodes, Elements = 81539 456167
AFLR3 GG : Nodes, Elements = 81539 456190
AFLR3 GG : Nodes, Elements = 81539 456179
AFLR3 GG : Nodes, Elements = 81543 456191
AFLR3 GG : Nodes, Elements = 81543 456211
AFLR3 GG : Nodes, Elements = 81543 456201
AFLR3 : CPU Time = 4.144 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 = 1.016 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 7.475771 -1.764585 3.704520 -0.192437 0.438788
1 7.348104 -1.665379 3.813117 0.033126 0.242902
2 7.204173 -1.655562 3.824904 0.168188 0.077505
3 7.210019 -1.751945 3.727511 0.205416 0.022590
------------------------ Evaluate Special Output ------------------------
Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat).
-------------------------------------------------------------------------
4 7.159723 -1.820189 3.650994 0.209024 0.012775
----------------------------- Solver Exit -------------------------------
Maximum number of external iterations reached (EXT_ITER).
-------------------------------------------------------------------------
-------------------------- File Output Summary --------------------------
Writing comma-separated values (CSV) surface files.
Loading solution output data locally on each rank.
Sorting output data across all ranks.
Writing binary SU2 native restart file.
Preparing element connectivity across all ranks.
Writing Tecplot ASCII file volume solution file.
Writing Tecplot ASCII file surface solution file.
-------------------------------------------------------------------------
------------------------- Solver Postprocessing -------------------------
Deleted CNumerics container.
Deleted CIntegration container.
Deleted CSolver container.
Deleted CIteration container.
Deleted CInterpolator container.
Deleted CTransfer container.
Deleted CGeometry container.
Deleted CFreeFormDefBox class.
Deleted CSurfaceMovement class.
Deleted CVolumetricMovement class.
Deleted CConfig container.
Deleted nInst container.
Deleted COutput class.
-------------------------------------------------------------------------
------------------------- Exit Success (SU2_CFD) ------------------------
==> Running SU2 post-analysis...
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
Number of variables = 7
Number of data points = 9015
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
Number of variables = 7
Number of data points = 9015
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
Number of variables = 7
Number of data points = 9015
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
Number of variables = 7
Number of data points = 9015
Executing dataTransfer "Pressure"......
Bound upperWing: Normalized Integrated Pressure
Rank=0: src=6.265700e+09, tgt=6.265700e+09, diff=3.835140e+01
Bound lowerWing: Normalized Integrated Pressure
Rank=0: src=6.102777e+09, tgt=6.102777e+09, diff=1.295066e+01
Bound leftTip: Normalized Integrated Pressure
Rank=0: src=6.123320e+07, tgt=6.123320e+07, diff=0.000000e+00
Bound riteTip: Normalized Integrated Pressure
Rank=0: src=6.125526e+07, tgt=6.125526e+07, diff=0.000000e+00
==> Running ASTROS pre-analysis...
Getting FEA materials.......
Number of materials - 2
Material name - Unobtainium
No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic"
Material name - Madeupium
Done getting FEA materials
Getting FEA properties.......
Number of properties - 5
Property name - leftWingSkin
Property name - riteWingSkin
Property name - wingRib
Property name - wingSpar1
Property name - wingSpar2
Done getting FEA properties
Updating mesh element types based on properties input
Getting FEA constraints.......
Number of constraints - 1
Constraint name - rootConstraint
No "constraintType" specified for Constraint tuple rootConstraint, defaulting to "ZeroDisplacement"
Done getting FEA constraints
Support tuple is NULL - No supports applied
Connect tuple is NULL - Using defaults
Getting FEA loads.......
Number of loads - 1
Load name - pressureAero
No "groupName" specified for Load tuple pressureAero, going to use load name
Done getting FEA loads
Extracting external pressure loads from data transfer....
TransferName = upperWing
Number of Elements = 96 (total = 96)
TransferName = lowerWing
Number of Elements = 96 (total = 192)
TransferName = leftTip
Number of Elements = 10 (total = 202)
TransferName = riteTip
Number of Elements = 10 (total = 212)
Design_Variable tuple is NULL - No design variables applied
Design_Constraint tuple is NULL - No design constraints applied
Analysis tuple is NULL
Getting FEA analyses.......
Number of analyses - 1
Analysis name - Default
Done getting FEA analyses
Writing Astros grid and connectivity file (in large field format) ....
Finished writing Astros grid file
Writing subElement types (if any) - appending mesh file
Writing Astros instruction file....
Writing analysis cards
Writing load ADD cards
Writing constraint cards--each subcase individually
Writing load cards
Writing material cards
Writing property cards
Writing coordinate system cards
Running Astros......
==> Running ASTROS post-analysis...
Executing dataTransfer "Displacement"......
==> Running SU2 pre-analysis...
Getting CFD boundary conditions
Boundary condition name - Wing
Boundary condition name - Farfield
Done getting CFD boundary conditions
Found link for volume mesh (Volume_Mesh) from parent
Writing boundary flags
- bcProps.surfaceProp[0].surfaceType = 1
- bcProps.surfaceProp[1].surfaceType = 3
Done boundary flags
Writing SU2 data transfer files
Writing SU2 Motion File - aeroelasticIterative_motion.dat
Warning: The su2 cfg file will be overwritten!
Write SU2 configuration file for version "Falcon"
Running SU2......
-------------------------------------------------------------------------
| ___ _ _ ___ |
| / __| | | |_ ) Release 6.2.0 "Falcon" |
| \__ \ |_| |/ / |
| |___/\___//___| Suite (Mesh Deformation Code) |
| |
-------------------------------------------------------------------------
| The current SU2 release has been coordinated by the |
| SU2 International Developers Society <www.su2devsociety.org> |
| with selected contributions from the open-source community. |
-------------------------------------------------------------------------
| The main research teams contributing to the current release are: |
| - Prof. Juan J. Alonso's group at Stanford University. |
| - Prof. Piero Colonna's group at Delft University of Technology. |
| - Prof. Nicolas R. Gauger's group at Kaiserslautern U. of Technology. |
| - Prof. Alberto Guardone's group at Polytechnic University of Milan. |
| - Prof. Rafael Palacios' group at Imperial College London. |
| - Prof. Vincent Terrapon's group at the University of Liege. |
| - Prof. Edwin van der Weide's group at the University of Twente. |
| - Lab. of New Concepts in Aeronautics at Tech. Inst. of Aeronautics. |
-------------------------------------------------------------------------
| Copyright 2012-2019, Francisco D. Palacios, Thomas D. Economon, |
| Tim Albring, and the SU2 contributors. |
| |
| SU2 is free software; you can redistribute it and/or |
| modify it under the terms of the GNU Lesser General Public |
| License as published by the Free Software Foundation; either |
| version 2.1 of the License, or (at your option) any later version. |
| |
| SU2 is distributed in the hope that it will be useful, |
| but WITHOUT ANY WARRANTY; without even the implied warranty of |
| MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU |
| Lesser General Public License for more details. |
| |
| You should have received a copy of the GNU Lesser General Public |
| License along with SU2. If not, see <http://www.gnu.org/licenses/>. |
-------------------------------------------------------------------------
------------------------ Physical Case Definition -----------------------
Input mesh file name: aeroelasticIterative.su2
---------------------- Grid deformation parameters ----------------------
Grid deformation using a linear elasticity method.
-------------------------- Output Information ---------------------------
Output mesh file name: aeroelasticIterative.su2.
A file will be created to visualize the surface deformation.
No file for visualizing the deformation.
Cell stiffness scaled by distance to nearest solid surface.
------------------- Config File Boundary Information --------------------
+-----------------------------------------+
| Marker Type| Marker Name|
+-----------------------------------------+
| Euler wall| 1|
+-----------------------------------------+
| Far-field| 2|
+-----------------------------------------+
---------------------- Read Grid File Information -----------------------
Three dimensional problem.
81087 points.
2 surface markers.
+------------------------------------+
| Index| Marker| Elements|
+------------------------------------+
| 0| 1| 18026|
| 1| 2| 636|
+------------------------------------+
452128 tetrahedra.
----------------------- Preprocessing computations ----------------------
Setting local point connectivity.
Checking the numerical grid orientation of the interior elements.
Identify edges and vertices.
Computing centers of gravity.
Setting the bound control volume structure.
Merging grid connectivity.
Merging grid coordinates.
Writing surface mesh file.
Writing .csv surface file.
--------------------- Surface grid deformation (ZONE 0) -----------------
Performing the deformation of the surface grid.
Updating the surface coordinates from the input file.
------------------- Volumetric grid deformation (ZONE 0) ----------------
Performing the deformation of the volumetric grid.
Computing volumes of the grid elements.
Min. volume: 1.30476e-06, max. volume: 4674.72.
Min. distance: 0.0169992, max. distance: 132.146.
# ILU preconditioner.
# FGMRES residual history
# Residual tolerance target = 1e-14
# Initial residual norm = 9.15648
0 1
10 0.00155825
20 3.18889e-05
30 3.50673e-06
40 5.8781e-07
50 6.3065e-08
60 2.96694e-09
70 1.19673e-10
80 4.53477e-12
90 1.70036e-13
100 2.86062e-14
110 2.816e-14
120 2.81594e-14
130 2.81594e-14
140 2.81594e-14
150 2.81594e-14
160 2.81594e-14
170 2.8136e-14
180 1.35735e-14
# FGMRES final (true) residual:
# Iteration = 182: |res|/|res0| = 7.74374e-15.
Computing volumes of the grid elements.
Non-linear iter.: 1/3. Linear iter.: 182. Min. volume: 1.25578. Error: 7.09054e-14.
Computing volumes of the grid elements.
Min. volume: 1.25578, max. volume: 4.73428e+10.
Min. distance: 4.409, max. distance: 12952.3.
# ILU preconditioner.
# FGMRES residual history
# Residual tolerance target = 1e-14
# Initial residual norm = 91994.7
0 1
10 0.00734772
20 0.00562794
30 0.00448978
40 0.0025112
50 0.00211445
60 0.0016828
70 0.00160343
80 0.00146444
90 0.00141096
100 0.00132886
110 0.00128244
120 0.00126405
130 0.00121126
140 0.00116279
150 0.00101357
160 0.000867317
170 0.000768805
180 0.000705568
190 0.000669162
200 0.000626613
210 0.000535373
220 0.000473201
230 0.000412394
240 0.000375247
250 0.000356338
260 0.000302262
270 0.000261247
280 0.000232062
290 0.0002104
300 0.000189482
310 0.000160919
320 0.00014318
330 0.000129237
340 0.000117224
350 0.000103776
360 9.54904e-05
370 8.94594e-05
380 8.74119e-05
390 8.51446e-05
400 8.27319e-05
410 7.96882e-05
420 7.53906e-05
430 7.38432e-05
440 7.18947e-05
450 7.03021e-05
460 6.77425e-05
470 6.48965e-05
480 6.19719e-05
490 5.73459e-05
500 5.57488e-05
# FGMRES final (true) residual:
# Iteration = 500: |res|/|res0| = 5.57488e-05.
# WARNING in CSysSolve::FGMRES_LinSolver():
# true residual norm and calculated residual norm do not agree.
# res = 5.12859, beta = 5.12859, tol = 1e-13.
# res - beta = 8.17577e-11
Computing volumes of the grid elements.
Non-linear iter.: 2/3. Linear iter.: 500. Min. volume: 5.15423. Error: 5.12859.
Computing volumes of the grid elements.
Min. volume: 5.15423, max. volume: 3.73141e+12.
Min. distance: 7.03807, max. distance: 72290.5.
# ILU preconditioner.
# FGMRES residual history
# Residual tolerance target = 1e-14
# Initial residual norm = 149485
0 1
10 0.00548596
20 0.00206638
30 0.00200579
40 0.00193331
50 0.00179781
60 0.00168381
70 0.00134777
80 0.00118803
90 0.00106996
100 0.000857073
110 0.000712221
120 0.000605828
130 0.000527313
140 0.000471176
150 0.000437766
160 0.000389888
170 0.000347891
180 0.000319542
190 0.000302576
200 0.00028891
210 0.000272393
220 0.000254702
230 0.000243022
240 0.000233567
250 0.000226707
260 0.000217414
270 0.000204045
280 0.000184671
290 0.00017227
300 0.000159396
310 0.000145279
320 0.000129636
330 0.000120155
340 0.000113431
350 0.000107013
360 0.000102719
370 9.88463e-05
380 9.46353e-05
390 8.9677e-05
400 8.39651e-05
410 7.61227e-05
420 6.92151e-05
430 6.44504e-05
440 6.14585e-05
450 5.9322e-05
460 5.79298e-05
470 5.53719e-05
480 5.39679e-05
490 5.22408e-05
500 5.06309e-05
# FGMRES final (true) residual:
# Iteration = 500: |res|/|res0| = 5.06309e-05.
# WARNING in CSysSolve::FGMRES_LinSolver():
# true residual norm and calculated residual norm do not agree.
# res = 7.56854, beta = 7.56854, tol = 1e-13.
# res - beta = -4.43197e-10
Computing volumes of the grid elements.
Non-linear iter.: 3/3. Linear iter.: 500. Min. volume: 5.32157. Error: 7.56854.
----------------------- Write deformed grid files -----------------------
Merging grid connectivity.
Merging grid coordinates.
Writing surface mesh file.
Writing .su2 file.
Writing .stl surface file.
Writing .csv surface file.
Adding any FFD information to the SU2 file.
------------------------- Solver Postprocessing -------------------------
Deleted CGeometry container.
Deleted CSurfaceMovement class.
Deleted CVolumetricMovement class.
Deleted CConfig container.
Deleted COutput class.
Completed in 238.007060 seconds on 1 core.
------------------------- Exit Success (SU2_DEF) ------------------------
-------------------------------------------------------------------------
| ___ _ _ ___ |
| / __| | | |_ ) Release 6.2.0 "Falcon" |
| \__ \ |_| |/ / |
| |___/\___//___| Suite (Computational Fluid Dynamics Code) |
| |
-------------------------------------------------------------------------
| The current SU2 release has been coordinated by the |
| SU2 International Developers Society <www.su2devsociety.org> |
| with selected contributions from the open-source community. |
-------------------------------------------------------------------------
| The main research teams contributing to the current release are: |
| - Prof. Juan J. Alonso's group at Stanford University. |
| - Prof. Piero Colonna's group at Delft University of Technology. |
| - Prof. Nicolas R. Gauger's group at Kaiserslautern U. of Technology. |
| - Prof. Alberto Guardone's group at Polytechnic University of Milan. |
| - Prof. Rafael Palacios' group at Imperial College London. |
| - Prof. Vincent Terrapon's group at the University of Liege. |
| - Prof. Edwin van der Weide's group at the University of Twente. |
| - Lab. of New Concepts in Aeronautics at Tech. Inst. of Aeronautics. |
-------------------------------------------------------------------------
| Copyright 2012-2019, Francisco D. Palacios, Thomas D. Economon, |
| Tim Albring, and the SU2 contributors. |
| |
| SU2 is free software; you can redistribute it and/or |
| modify it under the terms of the GNU Lesser General Public |
| License as published by the Free Software Foundation; either |
| version 2.1 of the License, or (at your option) any later version. |
| |
| SU2 is distributed in the hope that it will be useful, |
| but WITHOUT ANY WARRANTY; without even the implied warranty of |
| MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU |
| Lesser General Public License for more details. |
| |
| You should have received a copy of the GNU Lesser General Public |
| License along with SU2. If not, see <http://www.gnu.org/licenses/>. |
-------------------------------------------------------------------------
------------------------ Physical Case Definition -----------------------
Compressible Euler equations.
Mach number: 0.294118.
Angle of attack (AoA): 0 deg, and angle of sideslip (AoS): 0 deg.
No restart solution, use the values at infinity (freestream).
Dimensional simulation.
The reference area is 10 m^2.
The semi-span will be computed using the max y(3D) value.
The reference length is 7.74597 m.
Reference origin for moment evaluation is (0.322749, 0, 0).
Surface(s) where the force coefficients are evaluated: 1.
Surface(s) plotted in the output file: 1.
Surface(s) affected by the design variables: 1.
Input mesh file name: aeroelasticIterative.su2
---------------------- Space Numerical Integration ----------------------
Roe (with entropy fix = 0.001) solver for the flow inviscid terms.
Roe with DDES's FD low-dissipation function.
Second order integration in space, with slope limiter.
Venkatakrishnan slope-limiting method, with constant: 0.05.
The reference element size is: 1.
Gradient computation using Green-Gauss theorem.
---------------------- Time Numerical Integration -----------------------
Local time stepping (steady state simulation).
Euler implicit method for the flow equations.
FGMRES is used for solving the linear system.
Using a ILU(0) preconditioning.
Convergence criteria of the linear solver: 1e-06.
Max number of linear iterations: 10.
V Multigrid Cycle, with 2 multigrid levels.
Damping factor for the residual restriction: 0.75.
Damping factor for the correction prolongation: 0.75.
No CFL adaptation.
+-------------------------------------------+
| MG Level| Presmooth|PostSmooth|CorrectSmo|
+-------------------------------------------+
| 0| 1| 0| 0|
| 1| 2| 0| 0|
| 2| 3| 0| 0|
+-------------------------------------------+
Courant-Friedrichs-Lewy number: 10
------------------------- Convergence Criteria --------------------------
Maximum number of iterations: 5.
Reduce the density residual 6 orders of magnitude.
The minimum bound for the density residual is 10^(-8).
Start convergence criteria at iteration 10.
-------------------------- Output Information ---------------------------
Writing a solution file every 1000 iterations.
Writing the convergence history every 1 iterations.
The output file format is Tecplot ASCII (.dat).
Convergence history file name: history_aeroelasticIterative.
Forces breakdown file name: forces_breakdown_aeroelasticIterative.dat.
Surface flow coefficients file name: surface_flow_aeroelasticIterative.
Flow variables file name: flow_aeroelasticIterative.
Restart flow file name: restart_flow_aeroelasticIterative.dat.
------------------- Config File Boundary Information --------------------
+-----------------------------------------+
| Marker Type| Marker Name|
+-----------------------------------------+
| Euler wall| 1|
+-----------------------------------------+
| Far-field| 2|
+-----------------------------------------+
---------------------- Read Grid File Information -----------------------
Three dimensional problem.
81087 points.
2 surface markers.
+------------------------------------+
| Index| Marker| Elements|
+------------------------------------+
| 0| 1| 18026|
| 1| 2| 636|
+------------------------------------+
452128 tetrahedra.
------------------------- Geometry Preprocessing ------------------------
Setting point connectivity.
Renumbering points (Reverse Cuthill McKee Ordering).
Recomputing point connectivity.
Setting element connectivity.
Checking the numerical grid orientation.
There has been a re-orientation of the TETRAHEDRON volume elements.
There has been a re-orientation of the TRIANGLE surface elements.
Identifying edges and vertices.
Computing centers of gravity.
Setting the control volume structure.
Volume of the computational grid: 2.77e+16.
Finding max control volume width.
Searching for the closest normal neighbors to the surfaces.
Storing a mapping from global to local point index.
Compute the surface curvature.
Max K: 2.54. Mean K: 0.0074. Standard deviation K: 0.049.
Checking for periodicity.
Setting the multigrid structure.
+-------------------------------------------+
| MG Level| CVs|Aggl. Rate| CFL|
+-------------------------------------------+
| 0| 81087| 1/1.00| 10|
| 1| 13387| 1/6.06| 8.23|
| 2| 2086| 1/6.42| 6.64|
+-------------------------------------------+
Semi-span length = 3.16e+04 m.
Wetted area = 2.04e+10 m^2.
Area projection in the x-plane = 8.67e+09 m^2, y-plane = 6.34e+09 m^2, z-plane = 5.99e+08 m^2.
Max. coordinate in the x-direction = 1.43e+03 m, y-direction = 3.16e+04 m, z-direction = 0.168 m.
Min coordinate in the x-direction = -1.5e+04 m, y-direction = -3.31e+04 m, z-direction = -3.63e+05 m.
------------------------- Driver information --------------------------
A Fluid driver has been instantiated.
------------------------ Iteration Preprocessing ------------------------
Zone 1: Euler/Navier-Stokes/RANS fluid iteration.
------------------------- Solver Preprocessing --------------------------
Inviscid flow: Computing density based on free-stream
temperature and pressure using the ideal gas law.
Force coefficients computed using free-stream values.
-- Models:
+------------------------------------------------------------------------------+
| Viscosity Model| Conductivity Model| Fluid Model|
+------------------------------------------------------------------------------+
| -| -| STANDARD_AIR|
+------------------------------------------------------------------------------+
-- Fluid properties:
+------------------------------------------------------------------------------+
| Name| Dim. value| Ref. value| Unit|Non-dim. value|
+------------------------------------------------------------------------------+
| Gas Constant| 287.058| 1| N.m/kg.K| 287.058|
| Spec. Heat Ratio| -| -| -| 1.4|
+------------------------------------------------------------------------------+
-- Initial and free-stream conditions:
+------------------------------------------------------------------------------+
| Name| Dim. value| Ref. value| Unit|Non-dim. value|
+------------------------------------------------------------------------------+
| Static Pressure| 101325| 1| Pa| 101325|
| Density| 1.22498| 1| kg/m^3| 1.22498|
| Temperature| 288.15| 1| K| 288.15|
| Total Energy| 211798| 1| m^2/s^2| 211798|
| Velocity-X| 100.087| 1| m/s| 100.087|
| Velocity-Y| 0| 1| m/s| 0|
| Velocity-Z| 0| 1| m/s| 0|
| Velocity Magnitude| 100.087| 1| m/s| 100.087|
+------------------------------------------------------------------------------+
| Mach Number| -| -| -| 0.294118|
+------------------------------------------------------------------------------+
Initialize Jacobian structure (Euler). MG level: 0.
Initialize Jacobian structure (Euler). MG level: 1.
Initialize Jacobian structure (Euler). MG level: 2.
----------------- Integration and Numerics Preprocessing ----------------
Integration Preprocessing.
Numerics Preprocessing.
---------------------- Python Interface Preprocessing ---------------------
Setting customized boundary conditions for zone 0
------------------------------ Begin Solver -----------------------------
------------------------ Evaluate Special Output ------------------------
Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat).
-------------------------------------------------------------------------
---------------------- Local Time Stepping Summary ----------------------
MG level: 0 -> Min. DT: 0.000131617. Max. DT: 400.624. CFL: 10.
MG level: 1 -> Min. DT: 0.0481787. Max. DT: 587.302. CFL: 8.22878.
MG level: 2 -> Min. DT: 0.14467. Max. DT: 698.218. CFL: 6.64207.
-------------------------------------------------------------------------
----------------------- Residual Evolution Summary ----------------------
log10[Maximum residual]: 12.1487.
Maximum residual point 34103, located at (153967, 82285.4, -203576).
There are 5869 non-physical points in the solution.
-------------------------------------------------------------------------
Iter Time(s) Res[Rho] Res[RhoE] CL(Total) CD(Total)
0 7.458394 10.314447 15.783553 -10000.000000 10000.000000
1 7.509117 10.956724 16.663628 -10000.000000 10000.000000
2 7.533435 11.082252 16.968784 -10000.000000 -10000.000000
3 7.588383 11.368463 17.483368 -10000.000000 10000.000000
------------------------ Evaluate Special Output ------------------------
Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat).
-------------------------------------------------------------------------
4 7.560310 11.556319 17.680648 -10000.000000 10000.000000
----------------------------- Solver Exit -------------------------------
Maximum number of external iterations reached (EXT_ITER).
-------------------------------------------------------------------------
-------------------------- File Output Summary --------------------------
Writing comma-separated values (CSV) surface files.
Loading solution output data locally on each rank.
Sorting output data across all ranks.
Writing binary SU2 native restart file.
Preparing element connectivity across all ranks.
Writing Tecplot ASCII file volume solution file.
Writing Tecplot ASCII file surface solution file.
-------------------------------------------------------------------------
Warning: there are 27384 non-physical points in the solution.
Warning: 2373 reconstructed states for upwinding are non-physical.
------------------------- Solver Postprocessing -------------------------
Deleted CNumerics container.
Deleted CIntegration container.
Deleted CSolver container.
Deleted CIteration container.
Deleted CInterpolator container.
Deleted CTransfer container.
Deleted CGeometry container.
Deleted CFreeFormDefBox class.
Deleted CSurfaceMovement class.
Deleted CVolumetricMovement class.
Deleted CConfig container.
Deleted nInst container.
Deleted COutput class.
-------------------------------------------------------------------------
------------------------- Exit Success (SU2_CFD) ------------------------
==> Running SU2 post-analysis...
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
Number of variables = 7
Number of data points = 9015
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
Number of variables = 7
Number of data points = 9015
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
Number of variables = 7
Number of data points = 9015
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
Number of variables = 7
Number of data points = 9015
Executing dataTransfer "Pressure"......
Bound upperWing: Normalized Integrated Pressure
Rank=0: src=3.952649e+10, tgt=3.952648e+10, diff=6.054567e+02
Bound lowerWing: Normalized Integrated Pressure
Rank=0: src=1.983030e+10, tgt=1.983030e+10, diff=8.194724e+02
Bound leftTip: Normalized Integrated Pressure
Rank=0: src=1.856825e+08, tgt=1.856825e+08, diff=3.707409e-05
Bound riteTip: Normalized Integrated Pressure
Rank=0: src=7.116292e+08, tgt=7.116292e+08, diff=0.000000e+00
==> Running ASTROS pre-analysis...
Getting FEA materials.......
Number of materials - 2
Material name - Unobtainium
No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic"
Material name - Madeupium
Done getting FEA materials
Getting FEA properties.......
Number of properties - 5
Property name - leftWingSkin
Property name - riteWingSkin
Property name - wingRib
Property name - wingSpar1
Property name - wingSpar2
Done getting FEA properties
Updating mesh element types based on properties input
Getting FEA constraints.......
Number of constraints - 1
Constraint name - rootConstraint
No "constraintType" specified for Constraint tuple rootConstraint, defaulting to "ZeroDisplacement"
Done getting FEA constraints
Support tuple is NULL - No supports applied
Connect tuple is NULL - Using defaults
Getting FEA loads.......
Number of loads - 1
Load name - pressureAero
No "groupName" specified for Load tuple pressureAero, going to use load name
Done getting FEA loads
Extracting external pressure loads from data transfer....
TransferName = upperWing
Number of Elements = 96 (total = 96)
TransferName = lowerWing
Number of Elements = 96 (total = 192)
TransferName = leftTip
Number of Elements = 10 (total = 202)
TransferName = riteTip
Number of Elements = 10 (total = 212)
Design_Variable tuple is NULL - No design variables applied
Design_Constraint tuple is NULL - No design constraints applied
Analysis tuple is NULL
Getting FEA analyses.......
Number of analyses - 1
Analysis name - Default
Done getting FEA analyses
Writing Astros grid and connectivity file (in large field format) ....
Finished writing Astros grid file
Writing subElement types (if any) - appending mesh file
Writing Astros instruction file....
Writing analysis cards
Writing load ADD cards
Writing constraint cards--each subcase individually
Writing load cards
Writing material cards
Writing property cards
Writing coordinate system cards
Running Astros......
==> Running ASTROS post-analysis...
--> temporary directory "tmp_OpenCSM_00" removed
Cleaning up aflr4Instance - 0
Cleaning up aflr3Instance - 0
Cleaning up su2Instance - 0
Cleaning up egadsInstance - 0
Cleaning up astrosInstance - 0
EGADS Info: 762 Objects, 1223 Reference in Use (of 29696) at Close!
real 9m7.572s
user 7m14.108s
sys 0m46.372s
+ status=0
+ set +x
=================================================
data/session11/aeroelastic_Iterative_SU2_Astros.py passed (as expected)
=================================================
*************************************************
*************************************************
=================================================
Did not run examples for:
session07
=================================================
All tests pass!
=================================================
=================================================
[Execution node] check if [macys_VM] is in [[windows10x64, windows7x64]]
Run condition [Execution node ] preventing perform for step [Execute Windows batch command]
[GNU C Compiler (gcc)] Sleeping for 5 seconds due to JENKINS-32191...
[GNU C Compiler (gcc)] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_QuickTestCaps/7.4/CAPS/training/DARWIN64')
[GNU C Compiler (gcc)] Successfully parsed console log
[GNU C Compiler (gcc)] -> found 0 issues (skipped 0 duplicates)
[GNU C Compiler (gcc)] Skipping post processing
[GNU C Compiler (gcc)] No filter has been set, publishing all 0 issues
[GNU C Compiler (gcc)] Repository miner is not configured, skipping mining
[Clang (LLVM based)] Sleeping for 5 seconds due to JENKINS-32191...
[Clang (LLVM based)] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_QuickTestCaps/7.4/CAPS/training/DARWIN64')
[Clang (LLVM based)] Successfully parsed console log
[Clang (LLVM based)] -> found 0 issues (skipped 0 duplicates)
[Clang (LLVM based)] Skipping post processing
[Clang (LLVM based)] No filter has been set, publishing all 0 issues
[Clang (LLVM based)] Repository miner is not configured, skipping mining
[Static Analysis] Reference build recorder is not configured
[Static Analysis] Obtaining reference build from same job (7.4,DARWIN64,macys_VM)
[Static Analysis] Using reference build 'ESP_QuickTestCaps/CASREV=7.4,ESP_ARCH=DARWIN64,buildnode=macys_VM #23' to compute new, fixed, and outstanding issues
[Static Analysis] Issues delta (vs. reference build): outstanding: 0, new: 0, fixed: 0
[Static Analysis] Evaluating quality gates
[Static Analysis] -> PASSED - Total (any severity): 0 - Quality QualityGate: 1
[Static Analysis] -> All quality gates have been passed
[Static Analysis] Health report is disabled - skipping
[Static Analysis] Created analysis result for 0 issues (found 0 new issues, fixed 0 issues)
[Static Analysis] Attaching ResultAction with ID 'analysis' to build 'ESP_QuickTestCaps/CASREV=7.4,ESP_ARCH=DARWIN64,buildnode=macys_VM #24'.
[Checks API] No suitable checks publisher found.
[PostBuildScript] - [INFO] Executing post build scripts.
[PostBuildScript] - [INFO] build step #0 should only be executed on MATRIX
[WS-CLEANUP] Deleting project workspace...
[WS-CLEANUP] done
Finished: SUCCESS
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