Missile Datcom Input & Output files

In summary, the conversation is about a person trying out a sample input file from a website, but they are unable to get the same output as shown. They share their input and output files and discuss errors and syntax issues. Additionally, there is a missing "NEXT CASE" card in the output file which is added in the final summary. The conversation also mentions using Newtonian impact theory and specifying dimensions in inches, as well as various variables and their assigned values.
  • #1
missileman
2
0
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:
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  • #2
The link in the OP is broken.
 
  • #3
Fixed. Thanks for telling.
 

FAQ: Missile Datcom Input & Output files

What is Missile Datcom Input & Output files?

Missile Datcom Input & Output files are computer files used in the aerospace industry to input data and output results for missile aerodynamics analysis. They contain information such as missile geometry, flight conditions, and aerodynamic coefficients.

What types of data are required in Missile Datcom Input files?

The main types of data required in Missile Datcom Input files are missile geometry, flight conditions, and control surface deflection data. This includes information such as wing and fuselage dimensions, Mach number, angle of attack, and control surface deflection angles.

How are Missile Datcom Input files used in aerodynamics analysis?

Missile Datcom Input files are used as input data for aerodynamics analysis programs such as Missile Datcom and XFOIL. These programs use the data to calculate aerodynamic coefficients and other important parameters for the missile's flight performance.

What types of results can be obtained from Missile Datcom Output files?

Missile Datcom Output files contain a variety of results, including aerodynamic coefficients, stability derivatives, and force and moment data. These results can be used to analyze the missile's flight characteristics and make design improvements.

Are Missile Datcom Input & Output files standardized?

Yes, Missile Datcom Input & Output files follow a standardized format to ensure compatibility between different analysis programs. However, some programs may have additional or different requirements for input data.

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