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Missile Datcom Input & Output files

  1. Jul 11, 2013 #1
    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: Jul 11, 2013
  2. jcsd
  3. Jul 11, 2013 #2

    SteamKing

    User Avatar
    Staff Emeritus
    Science Advisor
    Homework Helper

    The link in the OP is broken.
     
  4. Jul 11, 2013 #3
    Fixed. Thanks for telling.
     
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