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July 11, 2013, 04:17 |
Missile Datcom
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#1 |
New Member
Bryan
Join Date: Jul 2013
Posts: 3
Rep Power: 12 |
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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