Missile Datcom Input & Output files

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SUMMARY

The discussion focuses on troubleshooting input and output files for the Missile DATCOM software, specifically version 3/99. The user encountered multiple input errors, including unknown variable names and missing equal signs, which resulted in discrepancies between expected and actual outputs. Key issues identified include the need for correct syntax and proper formatting of input parameters, such as the $FLTCON and $REFQ sections. The conversation highlights the importance of adhering to the software's input requirements to achieve accurate aerodynamic analysis.

PREREQUISITES
  • Understanding of Missile DATCOM software, specifically version 3/99
  • Familiarity with aerodynamic input parameters such as NMACH, MACH, and ALPHA
  • Knowledge of input file syntax and structure for simulation software
  • Experience with error codes and debugging in computational analysis tools
NEXT STEPS
  • Review the Missile DATCOM User Manual for detailed input specifications
  • Learn about common error codes and their resolutions in Missile DATCOM
  • Explore best practices for formatting input files in aerodynamic simulations
  • Investigate alternative aerodynamic analysis tools for comparison
USEFUL FOR

Aerospace engineers, simulation analysts, and anyone involved in aerodynamic modeling using Missile DATCOM will benefit from this discussion.

missileman
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Hi, I'm trying out this sample input file from this website (http://www.phoenix-int.com/~AnalysisServer/FileWrapper/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 ***
 
Last edited:
Engineering news on Phys.org
The link in the OP is broken.
 
Fixed. Thanks for telling.