$ $ original file qsetup.dat - test bed for getting qkks from external db $ $ this file simulates making a set of aics with an external program $ it generates two qkks matrices at different mach numbers, $ performs operations on them to make them into aic matrices $ then stores each on an output4 tape $ file alt51 from doug's tinynast model assign output4='aic.5',unit=25,delete $ file with aic for mach=0.5 assign output4='aic.6',unit=26,delete $ file with aic for mach=0.6 DIAG 8 $ time 10 SOL 144 $ STATIC AERO compile pfaero list noref $ alter 'endif $ noqkks' $ inside loop for making qkks type parm,,i,n,iunit=25 $ use units 25, 26, ... trnsp qkks/aic $ this is the definition of external program's aic matrix output4 aic,,,,///iunit $ iunit = iunit + 1 $ increment for each loop $alter 'endif $ noqkks'(,2) $ after loop end alter 'enddo.*lpflg' $ exit $ cend $ TITLE = RECTANGULAR WING FOR client DEMONSTRATION qsetup SUBTI = SYMMETRIC FLIGHT CONDITIONS, DOUBLET-LATTICE AERO $LABEL = HALF-SPAN MODEL, STATIC SYMMETRIC LOADING, default for aesmeth label = put aics on two tapes, then exit ECHO = BOTH SPC = 10 $ SYMMETRIC CONSTRAINTS mpc = 200 $ symmetric constraints DISP = ALL $ PRINT ALL DISPLACEMENTS STRESS = ALL $ PRINT ALL STRESSES FORCE = ALL $ PRINT ALL FORCES AEROF = ALL $ PRINT ALL AERODYNAMIC FORCES $ APRES = ALL $ PRINT ALL AERODYNAMIC PRESSURES SUBCASE 1 label = mach number is 0.5 TRIM = 1 $ 1 G LEVEL FLIGHT (LOW Q SIMULATES RIGID AIRFRAME) subcase 2 label = mach number is 0.6 trim = 2 $OUTPUT(PLOT) $ PLOTTER = NASTRAN $ SET 1 = ALL $ FIND SCALE, ORIGIN 1,SET 1 $ PLOT SET 1 $ PLOT STATIC DEFORMATION 0, ORIGIN 1, SET 1, OUTLINE BEGIN BULK param, aesmeth, direct $ temp $ because param, aesmeth is not present, the default of $ 'direct' is used, which selects the solver used prior to v70.5 $ GRID 1 0.0 0.0 0.5 GRID 2 0.0 0.0 -0.5 GRID 3 0.0 25.0 0.5 456 GRID 4 0.0 25.0 -0.5 456 GRID 5 0.0 50.0 0.5 456 GRID 6 0.0 50.0 -0.5 456 GRID 7 10.0 0.0 0.5 GRID 8 10.0 0.0 -0.5 GRID 9 10.0 25.0 0.5 456 GRID 10 10.0 25.0 -0.5 456 GRID 11 10.0 50.0 0.5 456 GRID 12 10.0 50.0 -0.5 456 GRID 13 20.0 0.0 0.5 GRID 14 20.0 0.0 -0.5 GRID 15 20.0 25.0 0.5 456 GRID 16 20.0 25.0 -0.5 456 GRID 17 20.0 50.0 0.5 456 GRID 18 20.0 50.0 -0.5 456 GRID 20 10.0 0.0 0.0 $ CQUAD4 11 199 1 2 4 3 CQUAD4 12 199 3 4 6 5 CQUAD4 15 199 11 5 6 12 CQUAD4 18 199 9 3 4 10 CQUAD4 19 199 15 9 10 16 CQUAD4 22 199 17 11 12 18 CQUAD4 24 199 13 14 16 15 CQUAD4 25 199 15 16 18 17 CQUAD4 27 199 7 8 10 9 CQUAD4 28 199 9 10 12 11 CQUAD4 29 199 1 2 8 7 CQUAD4 30 199 7 8 14 13 $ CROD 1 299 1 2 CROD 2 299 3 4 CROD 3 299 5 6 CROD 4 299 7 8 CROD 5 299 9 10 CROD 6 299 11 12 CROD 7 299 13 14 CROD 8 299 15 16 CROD 9 299 17 18 $ CQUAD4 13 96 7 1 3 9 0.0 CQUAD4 20 96 13 7 9 15 0.0 CQUAD4 14 97 9 3 5 11 0.0 CQUAD4 21 97 15 9 11 17 0.0 CQUAD4 17 98 8 2 4 10 0.0 CQUAD4 26 98 14 8 10 16 0.0 CQUAD4 16 99 10 4 6 12 0.0 CQUAD4 23 99 16 10 12 18 0.0 $ CONM2 10 20 200.0 -10.0 BC3 +C3 1000. 22500. 22500. PARAM WTMASS 2.588E-3 PARAM aunits 2.588E-3 $ MAT1 1 10.E6 0.3 0.1 CMAT1 +MAT1 20.+5 15.0+5 12.0+5 MAT1 90 10.E6 0.3 0.1 CMAT90 +MAT90 20.+3 15.0+3 12.0+3 $ PSHELL 199 1 0.05 PROD 299 1 0.01 PSHELL 96 90 0.20 PSHELL 97 90 0.20 PSHELL 98 90 0.20 PSHELL 99 90 0.20 $ $ SYMMETRIC BOUNDARY CONDITION $ SPC1 10 12456 20 SPC1, 10, 2456, 1 14, 2, 13 rbar, 207, 20, 7, 123456 rbar, 208, 20, 8, 123456 $MPC 200 7 3 1.0 20 3 -1.0 $MPC 200 7 1 1.0 20 5 -0.5 $MPC 200 8 3 1.0 20 3 -1.0 $MPC 200 8 1 1.0 20 5 0.5 SUPORT 20 3 $ $ AERODYNAMIC MODEL $ $ ACSID RCSID REFC REFB REFS SYMXZ SYMXY $AEROS 100 10.0 40.0 200.0 1 AEROS 100 20.0 50.0 1000.0 1 cord2r 100 10.0 0.0 0.0 10.0 0.0 10.0 20.0 0.0 0.0 $ $ WING DATA $ CAERO1 1100 1000 1 24 1 $ ( FWD LEFT POINT ) CHORD ( FWD RIGHT POINT ) CHORD $ X1 Y1 Z1 X12 X4 Y4 Z4 X14 0. 0. 0. 20. 0.0 50.0 0.0 20. $ $ $ THE PAERO1 CARD IS REQUIRED EVEN THOUGH IT IS NON-FUNCTIONAL $ $ (BECAUSE THERE ARE NO ASSOCIATED BODIES IN THIS EXAMPLE). $ $ $ $ PID B1 B2 B3 B4 B5 B6 PAERO1 1000 $ ID LABEL AESTAT 501 ANGLEA $AESTAT 502 PITCH AESTAT 503 URDD3 $AESTAT 504 URDD5 $ $ CONNECTIVITY OF AERO AND STRUCTURAL MODEL SPLINE1 1601 1100 1100 1123 1100 0. $ SET1 1100 1 3 5 9 11 13 20 15 17 $ ID MACH Q LABEL1 UX1 LABEL2 UX2 +TRM TRIM 1 0.5 1.0 URDD3 1.0 TRIM 2 0.6 1.0 URDD3 1.1 $param usetprt 11 dmi afaux 0 2 1 1 24 1 dmi afaux 1 1 0.0 4.0 8.0 12.0 16.0 20.0 0.0 4.0 8.0 12.0 16.0 20.0 0.0 4.0 8.0 12.0 16.0 20.0 0.0 4.0 8.0 12.0 16.0 20.0 ENDDATA COMPILE SAERSENS LIST NOREF $ SAERSENS alTER 'FBS.*/DUAL','' $ call fbsi LSALL, DPSAL,gtkl,qkks/DUAL $ alTER 'FBS.*/DUL','' $ call fbsi LSALL, DPLX,gtkl,qkks/DUL $ alTER 'FBS.*/ARLR','' $ call fbsi LSALL, KSALR,gtkl,qkks/ARLR $ alTER 'FBS.*/AMLR','' $ call fbsi LSALL, MSLR,gtkl,qkks/AMLR $ alTER 'FBS.*/DUALP','' $ call fbsi LSALL, DPSALU,gtkl,qkks/DUALP $ alTER 'FBS.*/DUALS','' $ call fbsi LSALL, PLSTBL,gtkl,qkks/DUALS $