ex11.out

Digital DATCOM Source Code and Examples

 THIS SOFTWARE AND ANY ACCOMPANYING DOCUMENTATION
 IS RELEASED "AS IS".  THE U.S. GOVERNMENT MAKES NO
 WARRANTY OF ANY KIND, EXPRESS OR IMPLIED, CONCERNING
 THIS SOFTWARE AND ANY ACCOMPANYING DOCUMENTATION,
 INCLUDING, WITHOUT LIMITATION, ANY WARRANTIES OF
 MERCHANTABILITY OR FITNESS FOR A PARTICULAR PURPOSE.
 IN NO EVENT WILL THE U.S. GOVERNMENT BE LIABLE FOR ANY
 DAMAGES, INCLUDING LOST PROFITS, LOST SAVINGS OR OTHER
 INCIDENTAL OR CONSEQUENTIAL DAMAGES ARISING OUT OF THE 
 USE, OR INABILITY TO USE, THIS SOFTWARE OR ANY
 ACCOMPANYING DOCUMENTATION, EVEN IF INFORMED IN ADVANCE
 OF THE POSSIBILITY OF SUCH DAMAGES.
  ****************************************************
  *    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  ******************************

  $FLTCON NMACH=1.0, MACH(1)=10.0, RNNUB(1)=1.06E5,                              
    NALPHA=5.0, ALSCHD(1)=0.0,5.0,10.0,15.0,20.0,                                
    HYPERS=.TRUE.$                                                               
  $OPTINS SREF=1.0, CBARR=1.0$                                                   
  $HYPEFF ALITD=15000.0, XHL=8.0, TWOTI=3.122, CF=2.0,                           
    HDELTA(1)=0.,2.,4.,6.,10.,12.,16.,20.,25.,30.,                               
    LAMNR=.TRUE., HNDLTA=10.0$                                                   
 CASEID FLAT PLATE WITH FLAP IN HYPERSONIC FLOW, EXAMPLE PROBLEM 11              
 NEXT CASE                                                                       
1          THE FOLLOWING IS A LIST OF ALL INPUT CARDS FOR THIS CASE.
0
  $FLTCON NMACH=1.0, MACH(1)=10.0, RNNUB(1)=1.06E5,                              
    NALPHA=5.0, ALSCHD(1)=0.0,5.0,10.0,15.0,20.0,                                
    HYPERS=.TRUE.$                                                               
  $OPTINS SREF=1.0, CBARR=1.0$                                                   
  $HYPEFF ALITD=15000.0, XHL=8.0, TWOTI=3.122, CF=2.0,                           
    HDELTA(1)=0.,2.,4.,6.,10.,12.,16.,20.,25.,30.,                               
    LAMNR=.TRUE., HNDLTA=10.0$                                                   
 CASEID FLAT PLATE WITH FLAP IN HYPERSONIC FLOW, EXAMPLE PROBLEM 11              
 NEXT CASE                                                                       
0 INPUT DIMENSIONS ARE IN FT, SCALE FACTOR IS 1.0000

 Return to main program from M01O01
 Return to main program from M50O62
 Return to main program from M02O02
 Return to main program from M51O63
                       AUTOMATED STABILITY AND CONTROL METHODS
  APRIL 1976 VERSION OF DATCOM
 AERODYNAMIC CONTROL EFFECTIVENESS AT HYPERSONIC SPEEDS
                                    FLAT PLATE WITH FLAP IN HYPERSONIC FLOW, EXAMPLE PROBLEM 11
                    MACH NUMBER=10.00                                                         REYNOLDS NO./FT= 0.11E+06

                    REF. AREA (FT2)=   1.000   LONG. REF. LENGTH(FT)=  1.000
 --INCREMENT IN NORMAL FORCE PER SPANWISE FOOT OF CONTROL------
    DELTA=      0.0      2.0      4.0      6.0     10.0     12.0     16.0     20.0     25.0     30.0
    alpha
 0.00E+00 0.00E+00 1.83E-02 3.97E-02 6.50E-02 1.13E-01 1.35E-01 1.73E-01 2.04E-01 2.34E-01 2.58E-01
 5.00E+00 0.00E+00 2.65E-02 7.33E-02 9.23E-02 1.50E-01 1.89E-01 2.90E-01 4.19E-01 6.15E-01 8.38E-01
 1.00E+01 0.00E+00 5.05E-02 1.22E-01 1.72E-01 3.14E-01 4.07E-01 6.37E-01 9.23E-01 1.34E+00 1.81E+00
 1.50E+01 0.00E+00 8.76E-02 2.06E-01 2.99E-01 5.60E-01 7.31E-01 1.15E+00 1.66E+00 2.42E+00 3.26E+00
 2.00E+01 0.00E+00 1.35E-01 3.19E-01 4.61E-01 8.59E-01 1.12E+00 1.76E+00 2.55E+00 3.70E+00 4.98E+00
 --INCREMENT IN AXIAL FORCE PER SPANWISE FOOT OF CONTROL-------
    DELTA=      0.0      2.0      4.0      6.0     10.0     12.0     16.0     20.0     25.0     30.0
    alpha
 0.00E+00 0.00E+00 6.39E-04 3.12E-04 1.19E-03 4.10E-03 5.96E-03 1.01E-02 1.44E-02 1.95E-02 2.45E-02
 5.00E+00 0.00E+00 9.26E-04-6.75E-04 9.80E-04 1.18E-02 2.26E-02 5.95E-02 1.22E-01 2.48E-01 4.36E-01
 1.00E+01 0.00E+00 1.76E-03 2.60E-03 9.15E-03 4.03E-02 6.84E-02 1.58E-01 3.05E-01 5.87E-01 9.98E-01
 1.50E+01 0.00E+00 3.06E-03 6.13E-03 1.90E-02 7.79E-02 1.30E-01 2.96E-01 5.63E-01 1.07E+00 1.81E+00
 2.00E+01 0.00E+00 4.70E-03 9.13E-03 2.86E-02 1.18E-01 1.98E-01 4.50E-01 8.58E-01 1.64E+00 2.77E+00
                       AUTOMATED STABILITY AND CONTROL METHODS
  APRIL 1976 VERSION OF DATCOM
 AERODYNAMIC CONTROL EFFECTIVENESS AT HYPERSONIC SPEEDS
                                    FLAT PLATE WITH FLAP IN HYPERSONIC FLOW, EXAMPLE PROBLEM 11
                    MACH NUMBER=10.00                                                         REYNOLDS NO./FT= 0.11E+06

                    REF. AREA (FT2)=   1.000   LONG. REF. LENGTH(FT)=  1.000
 -INCREMENT IN PITCHING MOMENT DUE TO NORMAL FORCE INCREMENT PER SPANWISE FOOT OF CONTROL---
    DELTA=      0.0      2.0      4.0      6.0     10.0     12.0     16.0     20.0     25.0     30.0
    alpha
 0.00E+00 0.00E+00-1.83E-02 1.43E-01 2.06E-01 3.34E-01 3.97E-01 5.14E-01 6.19E-01 7.31E-01 8.29E-01
 5.00E+00 0.00E+00-2.65E-02 5.22E-01 2.16E-01 6.66E-02 3.70E-04-1.46E-01-3.13E-01-5.37E-01-7.61E-01
 1.00E+01 0.00E+00-5.05E-02 1.65E-01 3.37E-03-2.14E-01-3.38E-01-6.24E-01-9.52E-01-1.39E+00-1.82E+00
 1.50E+01 0.00E+00-8.75E-02 1.13E-01-1.05E-01-4.73E-01-6.89E-01-1.19E+00-1.77E+00-2.54E+00-3.29E+00
 2.00E+01 0.00E+00-1.34E-01 2.08E-01-1.42E-01-7.09E-01-1.04E+00-1.81E+00-2.70E+00-3.88E+00-5.03E+00
 --INCREMENT IN PITCHING MOMENT DUE TO AXIAL FORCE INCREMENT PER SPANWISE FOOT OF CONTROL---
    DELTA=      0.0      2.0      4.0      6.0     10.0     12.0     16.0     20.0     25.0     30.0
    alpha
 0.00E+00 0.00E+00-2.23E-05 9.15E-06-9.43E-05-7.60E-04-1.35E-03-2.99E-03-5.08E-03-7.99E-03-1.12E-02
 5.00E+00 0.00E+00-3.23E-05 1.82E-03 7.39E-04-2.56E-03-6.72E-03-2.43E-02-6.11E-02-1.49E-01-3.03E-01
 1.00E+01 0.00E+00-6.15E-05 3.45E-04-1.01E-03-9.61E-03-1.95E-02-5.91E-02-1.39E-01-3.23E-01-6.39E-01
 1.50E+01 0.00E+00-1.07E-04 1.42E-05-2.38E-03-1.81E-02-3.61E-02-1.07E-01-2.49E-01-5.76E-01-1.13E+00
 2.00E+01 0.00E+00-1.64E-04 1.44E-04-3.54E-03-2.76E-02-5.51E-02-1.64E-01-3.81E-01-8.82E-01-1.74E+00
                       AUTOMATED STABILITY AND CONTROL METHODS
  APRIL 1976 VERSION OF DATCOM
 AERODYNAMIC CONTROL EFFECTIVENESS AT HYPERSONIC SPEEDS
                                    FLAT PLATE WITH FLAP IN HYPERSONIC FLOW, EXAMPLE PROBLEM 11
                    MACH NUMBER=10.00                                                         REYNOLDS NO./FT= 0.11E+06

                    REF. AREA (FT2)=   1.000   LONG. REF. LENGTH(FT)=  1.000
 ----- CENTER-OF-PRESSURE LOCATION OF NORMAL FORCE----------
    DELTA=      0.0      2.0      4.0      6.0     10.0     12.0     16.0     20.0     25.0     30.0
    alpha
 0.00E+00 3.40E+38-9.99E-01 3.60E+00 3.17E+00 2.96E+00 2.95E+00 2.97E+00 3.04E+00 3.13E+00 3.21E+00
 5.00E+00 3.40E+38-9.99E-01 7.12E+00 2.34E+00 4.44E-01 1.96E-03-5.03E-01-7.45E-01-8.74E-01-9.07E-01
 1.00E+01 3.40E+38-9.99E-01 1.35E+00 1.96E-02-6.83E-01-8.31E-01-9.79E-01-1.03E+00-1.04E+00-1.00E+00
 1.50E+01 3.40E+38-9.99E-01 5.49E-01-3.52E-01-8.44E-01-9.43E-01-1.04E+00-1.06E+00-1.05E+00-1.01E+00
 2.00E+01 3.40E+38-9.99E-01 6.53E-01-3.08E-01-8.26E-01-9.31E-01-1.03E+00-1.06E+00-1.05E+00-1.01E+00
 ----------CENTER-OF-PRESSURE LOCATION OF AXIAL FORCE---------
    DELTA=      0.0      2.0      4.0      6.0     10.0     12.0     16.0     20.0     25.0     30.0
    alpha
 0.00E+00 3.40E+38 3.49E-02-2.94E-02 7.90E-02 1.85E-01 2.26E-01 2.95E-01 3.52E-01 4.09E-01 4.58E-01
 5.00E+00 3.40E+38 3.49E-02 2.70E+00-7.54E-01 2.17E-01 2.97E-01 4.08E-01 4.99E-01 6.02E-01 6.95E-01
 1.00E+01 3.40E+38 3.49E-02-1.33E-01 1.10E-01 2.38E-01 2.86E-01 3.73E-01 4.55E-01 5.51E-01 6.40E-01
 1.50E+01 3.40E+38 3.49E-02-2.31E-03 1.25E-01 2.33E-01 2.78E-01 3.62E-01 4.42E-01 5.37E-01 6.25E-01
 2.00E+01 3.40E+38 3.49E-02-1.58E-02 1.24E-01 2.33E-01 2.79E-01 3.64E-01 4.44E-01 5.38E-01 6.27E-01
 Return to main program from M57O71
1          THE FOLLOWING IS A LIST OF ALL INPUT CARDS FOR THIS CASE.
0
1 END OF JOB.