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 ***
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: