ex4.out

Digital DATCOM Source Code and Examples

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  ****************************************************
  *    USAF STABILITY AND CONTROL  DIGITAL DATCOM    *
  *    PROGRAM REV. JAN 96   DIRECT INQUIRIES TO:    *
  *    WRIGHT LABORATORY  (WL/FIGC)  ATTN: W. BLAKE  *
  *      WRIGHT PATTERSON AFB, OHIO  45433           *
  *    PHONE [phone],   FAX [phone]    *
  ****************************************************
 Preparing to start the big loop
 At 1000
1                         CONERR - INPUT ERROR CHECKING
0 ERROR CODES - N* DENOTES THE NUMBER OF OCCURENCES OF EACH ERROR
0 A - UNKNOWN VARIABLE NAME
0 B - MISSING EQUAL SIGN FOLLOWING VARIABLE NAME
0 C - NON-ARRAY VARIABLE HAS AN ARRAY ELEMENT DESIGNATION - (N)
0 D - NON-ARRAY VARIABLE HAS MULTIPLE VALUES ASSIGNED
0 E - ASSIGNED VALUES EXCEED ARRAY DIMENSION
0 F - SYNTAX ERROR

0******************************  INPUT DATA CARDS  ******************************

  $FLTCON  NMACH=1.0, MACH(1)=0.6,                                               
   NALPHA=5.0, ALSCHD(1)=0.0,5.0,10.0,15.0,20.0, RNNUB(1)=3.1E6$                 
  $OPTINS SREF=694.2, CBARR=18.07, BLREF=45.6$                                   
  $SYNTHS XCG=36.68, ZCG=0.0$                                                    
  $BODY NX=19.0,BNOSE=2.0,BTAIL=1.0,BLN=1.46,BLA=1.97,                           
    X(1)=0.0, 2.01, 5.49, 8.975, 12.47, 15.97, 19.47, 22.89, 30.0,               
      33.51, 37.02, 40.53, 44.03, 47.53, 51.02, 54.52, 57.99, 60.0,              
    S(1)=0.0, 2.89, 7.42, 11.32, 14.64, 17.36, 19.49, 21.0, 21.91, 22.20,        
      21.90, 21.0, 19.49, 17.36, 14.64, 11.33, 7.42, 2.89, 0.0,                  
    P(1)=0.0, 1.84, 4.72, 7.21, 9.32, 11.01, 12.41, 13.36, 13.94, 14.14,         
      13.94, 13.36, 12.41, 11.05, 9.32, 7.21, 4.72, 1.84, 0.0,                   
    R(1)=0.0, 0.293, 0.752, 1.15, 1.48, 1.76, 1.97, 2.13, 2.22, 2.25,            
      2.22, 2.13, 1.97, 1.76, 1.48, 1.15, 0.752, 0.293, 0.0$                     
 NACA-W-6-65A004                                                                 
 NACA-H-6-65A004                                                                 
  $WGPLNF CHRDTP=0.346,SSPNE=1.29,SSPN=1.5,CHRDR=1.16,SAVSI=45.0,CHSTAT=0.25,    
   SWAFP=0.0,TWISTA=0.0,SSPNDD=0.0,DHDADI=0.0,DHDADO=0.0,TYPE=1.0$               
  $WGSCHR TOVC=.03,DELTAY=1.3,XOVC=0.4,CLI=0.0,ALPHAI=0.0,CLALPA(1)=0.131,       
   CLMAX(1)=.82,CMO=0.0,LERI=.0025,CLAMO=.105$                                   
  $VTPLNF CHRDTP=.42,SSPNE=.63,SSPN=1.5,CHRDR=1.02,SAVSI=28.1,                   
   CHSTAT=.25,SWAFP=0.0,TWISTA=0.0,TYPE=0.0$                                     
  $WGSCHR  $                                                                     
  $HTPLNF  SSPNE=21.34, SSPN=22.82, CHRDR=20.62, SAVSI=30.52, CHSTAT=0.0,        
    CHRDTP=3.80, SWAFP=0.0, TWISTA=0.0, SSPNDD=0.0,                              
    DHDADI=0.0, DHDADO=0.0, TYPE=1.0,SHB(1)=73.5$                                
 CASEID BODY PLUS WING PLUS CANARD, EXAMPLE PROBLEM 4, CASE 1                    
 SAVE                                                                            
 NEXT CASE                                                                       
 DIM M                                                                           
  $FLTCON NMACH=1.0, MACH(1)=2.0, RNNUB=6.56E6,                                  
    NALPHA=5.0, ALSCHD(1)=0.0,5.0,10.0,15.0,20.0,                                
    NALT=1.0, ALT(1)=27400.0$                                                    
 CASEID BODY PLUS WING PLUS CANARD, EXAMPLE PROBLEM 4, CASE 2                    
 NEXT CASE                                                                       
1          THE FOLLOWING IS A LIST OF ALL INPUT CARDS FOR THIS CASE.
0
  $FLTCON  NMACH=1.0, MACH(1)=0.6,                                               
   NALPHA=5.0, ALSCHD(1)=0.0,5.0,10.0,15.0,20.0, RNNUB(1)=3.1E6$                 
  $OPTINS SREF=694.2, CBARR=18.07, BLREF=45.6$                                   
  $SYNTHS XCG=36.68, ZCG=0.0$                                                    
  $BODY NX=19.0,BNOSE=2.0,BTAIL=1.0,BLN=1.46,BLA=1.97,                           
    X(1)=0.0, 2.01, 5.49, 8.975, 12.47, 15.97, 19.47, 22.89, 30.0,               
      33.51, 37.02, 40.53, 44.03, 47.53, 51.02, 54.52, 57.99, 60.0,              
    S(1)=0.0, 2.89, 7.42, 11.32, 14.64, 17.36, 19.49, 21.0, 21.91, 22.20,        
      21.90, 21.0, 19.49, 17.36, 14.64, 11.33, 7.42, 2.89, 0.0,                  
    P(1)=0.0, 1.84, 4.72, 7.21, 9.32, 11.01, 12.41, 13.36, 13.94, 14.14,         
      13.94, 13.36, 12.41, 11.05, 9.32, 7.21, 4.72, 1.84, 0.0,                   
    R(1)=0.0, 0.293, 0.752, 1.15, 1.48, 1.76, 1.97, 2.13, 2.22, 2.25,            
      2.22, 2.13, 1.97, 1.76, 1.48, 1.15, 0.752, 0.293, 0.0$                     
 NACA-W-6-65A004                                                                 
 NACA-H-6-65A004                                                                 
  $WGPLNF CHRDTP=0.346,SSPNE=1.29,SSPN=1.5,CHRDR=1.16,SAVSI=45.0,CHSTAT=0.25,    
   SWAFP=0.0,TWISTA=0.0,SSPNDD=0.0,DHDADI=0.0,DHDADO=0.0,TYPE=1.0$               
  $WGSCHR TOVC=.03,DELTAY=1.3,XOVC=0.4,CLI=0.0,ALPHAI=0.0,CLALPA(1)=0.131,       
   CLMAX(1)=.82,CMO=0.0,LERI=.0025,CLAMO=.105$                                   
  $VTPLNF CHRDTP=.42,SSPNE=.63,SSPN=1.5,CHRDR=1.02,SAVSI=28.1,                   
   CHSTAT=.25,SWAFP=0.0,TWISTA=0.0,TYPE=0.0$                                     
  $WGSCHR  $                                                                     
  $HTPLNF  SSPNE=21.34, SSPN=22.82, CHRDR=20.62, SAVSI=30.52, CHSTAT=0.0,        
    CHRDTP=3.80, SWAFP=0.0, TWISTA=0.0, SSPNDD=0.0,                              
    DHDADI=0.0, DHDADO=0.0, TYPE=1.0,SHB(1)=73.5$                                
 CASEID BODY PLUS WING PLUS CANARD, EXAMPLE PROBLEM 4, CASE 1                    
 SAVE                                                                            
 NEXT CASE                                                                       
0 INPUT DIMENSIONS ARE IN FT, SCALE FACTOR IS 1.0000

 Return to main program from M01O01
1                             AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM   
                                                        WING SECTION DEFINITION
0                                 IDEAL ANGLE OF ATTACK =   0.00000 DEG.

                              ZERO LIFT ANGLE OF ATTACK =   0.00000 DEG.

                                 IDEAL LIFT COEFFICIENT =   0.00000

                  ZERO LIFT PITCHING MOMENT COEFFICIENT =   0.00000

                             MACH ZERO LIFT-CURVE-SLOPE =   0.10052 /DEG.

                                    LEADING EDGE RADIUS =   0.00112 FRACTION CHORD

                              MAXIMUM AIRFOIL THICKNESS =   0.04000 FRACTION CHORD

                                                DELTA-Y =   0.83905 PERCENT CHORD


1                             AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM   
                                                   HORIZONTAL TAIL SECTION DEFINITION
0                                 IDEAL ANGLE OF ATTACK =   0.00000 DEG.

                              ZERO LIFT ANGLE OF ATTACK =   0.00000 DEG.

                                 IDEAL LIFT COEFFICIENT =   0.00000

                  ZERO LIFT PITCHING MOMENT COEFFICIENT =   0.00000