Missile Datcom
Not quite sure if this is the right place to ask this, but I'll go with it anyway.
I'm trying out this sample input file from this website (http://www.phoenix-int.com/~Analysis...r/example.html), but I couldn't get the same output as shown. Below are my input and output files: INPUT FILE: *------------------------------------------------------------------------ CASEID HYPMIS * Use newtonian imact theory. HYPER * Dimensions are in inches DIM IN * *---------------------------------------------------------------------------- * $FLTCON NMACH=1.0,MACH=1.0,ALT=0.0,NALPHA=2.0,ALPHA(1)=10. 0,0.0,BETA=0.0,$ * *---------------------------------------------------------------------------- * $REFQ XCG=81.0,LREF=21.0,SREF =346.4,SCALE=1.0,ROUGH=2.5E-4,BLAYER=TURB,$ * *---------------------------------------------------------------------------- * * BODY $AXIBOD TAFT=0.0,LAFT=20.0,DAFT=20.0,DEXIT=16.0,TNOSE=CONE ,LNOSE=20.0,$ $AXIBOD DNOSE=20.0,LCENTR=140.0,DCENTR=20.0,$ * *---------------------------------------------------------------------------- * * TAILS WITH FOUR PANELS $FINSET1 SECTYP=ARC,ZUPPER=0.04,LMAXU=0.4,0.4,LFLATU=0.0,0. 0,SSPAN=10.0,15.0,$ $FINSET1 CHORD=20.0,10.8,SWEEP=30.0,XLE=0.0,STA=0.0,NPANEL= 4.0,$ $FINSET1 PHIF=45.0,135.0,225.0,315.0,$ $TRIM SET=1.0,PANL1=.TRUE.,PANL2=.TRUE.,PANL3=.TRUE.,PAN L4=.TRUE.,$ PART SAVE NEXT CASE OUTPUT FILE: 1 ***** THE USAF AUTOMATED MISSILE DATCOM * REV 3/99 ***** AERODYNAMIC METHODS FOR MISSILE CONFIGURATIONS CONERR - INPUT ERROR CHECKING ERROR CODES - N* DENOTES THE NUMBER OF OCCURENCES OF EACH ERROR A - UNKNOWN VARIABLE NAME B - MISSING EQUAL SIGN FOLLOWING VARIABLE NAME C - NON-ARRAY VARIABLE HAS AN ARRAY ELEMENTDESIGNATION - (N) D - NON-ARRAY VARIABLE HAS MULTIPLE VALUES ASSIGNED E - ASSIGNED VALUES EXCEED ARRAY DIMENSION F - SYNTAX ERROR ************************* INPUT DATA CARDS ************************* 1 *------------------------------------------------------------------------ 2 CASEID HYPMIS 3 * Use newtonian imact theory. 4 HYPER 5 * Dimensions are in inches 6 DIM IN 7 * 8 *---------------------------------------------------------------------------- 9 * 10 $FLTCON NMACH=1.0,MACH=1.0,ALT=0.0,NALPHA=2.0,ALPHA(1)=10. 0,0.0,BETA=0.0,$ 11 * 12 *---------------------------------------------------------------------------- 13 * 14 $REFQ XCG=81.0,LREF=21.0,SREF =346.4,SCALE=1.0,ROUGH=2.5E-4,BLAYER=TURB,$ ** SUBSTITUTING NUMERIC FOR NAME TURB 15 * 16 *---------------------------------------------------------------------------- 17 * 18 * BODY 19 $AXIBOD TAFT=0.0,LAFT=20.0,DAFT=20.0,DEXIT=16.0,TNOSE=CONE ,LNOSE=20.0,$ ** SUBSTITUTING NUMERIC FOR NAME CONE 20 $AXIBOD DNOSE=20.0,LCENTR=140.0,DCENTR=20.0,$ 21 * 22 *---------------------------------------------------------------------------- 23 * 24 * TAILS WITH FOUR PANELS 25 $FINSET1 SECTYP=ARC,ZUPPER=0.04,LMAXU=0.4,0.4,LFLATU=0.0,0. 0,SSPAN=10.0,15.0,$ ** SUBSTITUTING NUMERIC FOR NAME ARC 26 $FINSET1 CHORD=20.0,10.8,SWEEP=30.0,XLE=0.0,STA=0.0,NPANEL= 4.0,$ 27 $FINSET1 PHIF=45.0,135.0,225.0,315.0,$ 28 $TRIM SET=1.0,PANL1=.TRUE.,PANL2=.TRUE.,PANL3=.TRUE.,PAN L4=.TRUE.,$ 29 PART 30 SAVE NEXT CASE ** MISSING NEXT CASE CARD ADDED ** 1 ***** THE USAF AUTOMATED MISSILE DATCOM * REV 3/99 ***** CASE 1 AERODYNAMIC METHODS FOR MISSILE CONFIGURATIONS PAGE 1 CASE INPUTS FOLLOWING ARE THE CARDS INPUT FOR THIS CASE *------------------------------------------------------------------------ CASEID HYPMIS * Use newtonian imact theory. HYPER * Dimensions are in inches DIM IN * *---------------------------------------------------------------------------- * $FLTCON NMACH=1.0,MACH=1.0,ALT=0.0,NALPHA=2.0,ALPHA(1)=10. 0,0.0,BETA=0.0,$ * *---------------------------------------------------------------------------- * $REFQ XCG=81.0,LREF=21.0,SREF =346.4,SCALE=1.0,ROUGH=2.5E-4,BLAYER=0.,$ * *---------------------------------------------------------------------------- * * BODY $AXIBOD TAFT=0.0,LAFT=20.0,DAFT=20.0,DEXIT=16.0,TNOSE=0.,L NOSE=20.0,$ $AXIBOD DNOSE=20.0,LCENTR=140.0,DCENTR=20.0,$ * *---------------------------------------------------------------------------- * * TAILS WITH FOUR PANELS $FINSET1 SECTYP=2.,ZUPPER=0.04,LMAXU=0.4,0.4,LFLATU=0.0,0.0 ,SSPAN=10.0,15.0,$ $FINSET1 CHORD=20.0,10.8,SWEEP=30.0,XLE=0.0,STA=0.0,NPANEL= 4.0,$ $FINSET1 PHIF=45.0,135.0,225.0,315.0,$ $TRIM SET=1.0,PANL1=.TRUE.,PANL2=.TRUE.,PANL3=.TRUE.,PAN L4=.TRUE.,$ PART SAVE NEXT CASE *** END OF JOB *** |
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