ex4.out

Digital DATCOM Source Code and Examples

                             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


0                         MACH= 0.6000 LIFT-CURVE-SLOPE =   0.13701 /DEG.      XAC =   0.25736
0*** WARNING *** V.T. NOT STRAIGHT TAPERED. UNIFORM SECTION ASSUMED.
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 WARNING - DUPLICATE X VALUES AT X =  1.0000000E-30 IN TBFUNX, CALLED FROM EQSPC1   FOR FIGURE DSED
 WARNING - DUPLICATE X VALUES AT X =  1.0000000E-30 IN TBFUNX, CALLED FROM EQSPC1   FOR FIGURE DSED
 WARNING - DUPLICATE X VALUES AT X =  1.0000000E-30 IN TBFUNX, CALLED FROM EQSPC1   FOR FIGURE DSED
 WARNING - DUPLICATE X VALUES AT X =  1.0000000E-30 IN TBFUNX, CALLED FROM EQSPC1   FOR FIGURE DSED
 WARNING - DUPLICATE X VALUES AT X =  1.0000000E-30 IN TBFUNX, CALLED FROM EQSPC1   FOR FIGURE DSED
 WARNING - DUPLICATE X VALUES AT X =  1.0000000E-30 IN TBFUNX, CALLED FROM EQSPC1   FOR FIGURE DSED
 WARNING - DUPLICATE X VALUES AT X =  1.0000000E-30 IN TBFUNX, CALLED FROM EQSPC1   FOR FIGURE DSED
 WARNING - DUPLICATE X VALUES AT X =  1.0000000E-30 IN TBFUNX, CALLED FROM EQSPC1   FOR FIGURE DSED
 WARNING - DUPLICATE X VALUES AT X =  1.0000000E-30 IN TBFUNX, CALLED FROM EQSPC1   FOR FIGURE DSED
 WARNING - DUPLICATE X VALUES AT X =  1.0000000E-30 IN TBFUNX, CALLED FROM EQSPC1   FOR FIGURE DSED
 WARNING - DUPLICATE X VALUES AT X =  1.0000000E-30 IN TBFUNX, CALLED FROM EQSPC1   FOR FIGURE DSED
 WARNING - DUPLICATE X VALUES AT X =  1.0000000E-30 IN TBFUNX, CALLED FROM EQSPC1   FOR FIGURE DSED
 WARNING - DUPLICATE X VALUES AT X =  1.0000000E-30 IN TBFUNX, CALLED FROM EQSPC1   FOR FIGURE DSED
 WARNING - DUPLICATE X VALUES AT X =  1.0000000E-30 IN TBFUNX, CALLED FROM EQSPC1   FOR FIGURE DSED
 WARNING - DUPLICATE X VALUES AT X =  1.0000000E-30 IN TBFUNX, CALLED FROM EQSPC1   FOR FIGURE DSED
 WARNING - DUPLICATE X VALUES AT X =  1.0000000E-30 IN TBFUNX, CALLED FROM EQSPC1   FOR FIGURE DSED
 WARNING - DUPLICATE X VALUES AT X =  1.0000000E-30 IN TBFUNX, CALLED FROM EQSPC1   FOR FIGURE DSED
 WARNING - DUPLICATE X VALUES AT X =  1.0000000E-30 IN TBFUNX, CALLED FROM EQSPC1   FOR FIGURE DSED
 WARNING - DUPLICATE X VALUES AT X =  1.0000000E-30 IN TBFUNX, CALLED FROM EQSPC1   FOR FIGURE DSED
 WARNING - DUPLICATE X VALUES AT X =  1.0000000E-30 IN TBFUNX, CALLED FROM EQSPC1   FOR FIGURE DSED
 WARNING - DUPLICATE X VALUES AT X = -NaN           IN TBFUNX, CALLED FROM WBCM     FOR FIGURE ALWB
 WARNING - DUPLICATE X VALUES AT X = -NaN           IN TBFUNX, CALLED FROM WBCM     FOR FIGURE ALWB
1                               AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
                                         CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
                                        WING-BODY-VERTICAL TAIL-HORIZONTAL TAIL CONFIGURATION
                                       BODY PLUS WING PLUS CANARD, EXAMPLE PROBLEM 4, CASE 1
 
 -----------------------  FLIGHT CONDITIONS  ------------------------           --------------  REFERENCE DIMENSIONS  ------------
  MACH    ALTITUDE   VELOCITY    PRESSURE    TEMPERATURE     REYNOLDS             REF.      REFERENCE LENGTH   MOMENT REF. CENTER
 NUMBER                                                       NUMBER              AREA       LONG.     LAT.     HORIZ      VERT
             FT       FT/SEC     LB/FT**2       DEG R         1/FT               FT**2        FT        FT        FT        FT
0 0.600                                                    3.1000E+06           694.200     18.070    45.600    36.680     0.000
0                                                               -------------------DERIVATIVE (PER DEGREE)-------------------
0 ALPHA     CD       CL       CM       CN       CA       XCP        CLA          CMA          CYB          CNB          CLB
0
    0.0             NDM       NA                        NA         NDM          NA           NDM        1.155E-03      NDM 
    5.0             NDM       NA                        NA         NDM          NA                                     NDM 
   10.0             NDM       NA                        NA         NDM          NA                                     NDM 
   15.0             NDM       NA                        NA         NDM          NA                                     NDM 
   20.0             NDM       NA                        NA         NDM          NA                                     NDM 
0NOTE - CANARD CONFIGURATION EFFECTIVE EPSOLN AND D(EPSOLN)/D(ALPHA) ARE AVAILABLE AS PARTIAL OUTPUT AND IN THE FACT ARRAY
0*** NDM PRINTED WHEN NO DATCOM METHODS EXIST
0*** NA PRINTED WHEN METHOD NOT APPLICABLE
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1          THE FOLLOWING IS A LIST OF ALL INPUT CARDS FOR THIS CASE.
0
 DIM M                                                                           
0 *** WARNING *** THIS IS A SAVE CASE AND THE DIMENSION SYSTEM HAS BEEN CHANGED

  $FLTCON NMACH=1.0, MACH(1)=2.0, RNNUB=6.56E6,                                  
    NALPHA=5.0, ALSCHD(1)=0.0,5.0,10.0,15.0,20.0,                                
    NALT=1.0, ALT(1)=27400.0$                                                    
 CASEID BODY PLUS WING PLUS CANARD, EXAMPLE PROBLEM 4, CASE 2                    
 NEXT CASE                                                                       
0 INPUT DIMENSIONS ARE IN M , SCALE FACTOR IS 1.0000

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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


0                                    *** CREST CRITICAL MACH NUMBER EXCEEDED ***

                                    CREST CRITICAL MACH =   0.85862

                                               LOCATION =   0.29167 FRACTION CHORD

                                       LIFT-CURVE-SLOPE =   0.17534 /DEG.
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

                             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


0                                    *** CREST CRITICAL MACH NUMBER EXCEEDED ***

                                    CREST CRITICAL MACH =   0.85862

                                               LOCATION =   0.29167 FRACTION CHORD

                                       LIFT-CURVE-SLOPE =   0.17534 /DEG.
0*** WARNING *** V.T. NOT STRAIGHT TAPERED. UNIFORM SECTION ASSUMED.
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