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Old   July 11, 2013, 04:17
Default Missile Datcom
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Bryan
Join Date: Jul 2013
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Missileman is on a distinguished road
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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