Импорт из ВВС США цифровые файлы DATCOM

Этот пример показывает, как принести Военно-воздушным силам США (USAF) Цифровые файлы DATCOM в среду MATLAB® с помощью программного обеспечения Aerospace Toolbox™.

Пример ВВС США цифровой файл DATCOM

Вот является демонстрационный входной файл для ВВС США Цифровым DATCOM для горизонтальной телом крылом вертикальной хвостом настройки хвоста, работающей на основе 5 альф, 2 Чисел Маха и 2 высот и вычисляющей статические и динамические производные:

type astdatcom.in
 $FLTCON NMACH=2.0,MACH(1)=0.1,0.2$
 $FLTCON NALT=2.0,ALT(1)=5000.0,8000.0$                        
 $FLTCON NALPHA=5.,ALSCHD(1)=-2.0,0.0,2.0,    
  ALSCHD(4)=4.0,8.0,LOOP=2.0$
 $OPTINS SREF=225.8,CBARR=5.75,BLREF=41.15$                                      
 $SYNTHS XCG=7.08,ZCG=0.0,XW=6.1,ZW=-1.4,ALIW=1.1,XH=20.2,                      
   ZH=0.4,ALIH=0.0,XV=21.3,ZV=0.0,VERTUP=.TRUE.$                                        
 $BODY NX=10.0,                          
   X(1)=-4.9,0.0,3.0,6.1,9.1,13.3,20.2,23.5,25.9,                       
   R(1)=0.0,1.0,1.75,2.6,2.6,2.6,2.0,1.0,0.0$                     
 $WGPLNF CHRDTP=4.0,SSPNE=18.7,SSPN=20.6,CHRDR=7.2,SAVSI=0.0,CHSTAT=0.25,   
   TWISTA=-1.1,SSPNDD=0.0,DHDADI=3.0,DHDADO=3.0,TYPE=1.0$                         
NACA-W-6-64A412
 $HTPLNF CHRDTP=2.3,SSPNE=5.7,SSPN=6.625,CHRDR=0.25,SAVSI=11.0,                 
   CHSTAT=1.0,TWISTA=0.0,TYPE=1.0$                                               
NACA-H-4-0012
 $VTPLNF CHRDTP=2.7,SSPNE=5.0,SSPN=5.2,CHRDR=5.3,SAVSI=31.3,                 
   CHSTAT=0.25,TWISTA=0.0,TYPE=1.0$                                               
NACA-V-4-0012
CASEID SKYHOGG BODY-WING-HORIZONTAL TAIL-VERTICAL TAIL CONFIG 
DAMP
NEXT CASE                                                                    

Вот выходной файл, сгенерированный ВВС США Цифровой DATCOM для той же горизонтальной телом крылом вертикальной хвостом настройки хвоста, работающей на основе 5 альф, 2 Чисел Маха и 2 высот:

type astdatcom.out
 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 (513) 255-6764,   FAX (513) 258-4054    *
                                        ****************************************************
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  ******************************

  $FLTCON NMACH=2.0,MACH(1)=0.1,0.2$                                             
  $FLTCON NALT=2.0,ALT(1)=5000.0,8000.0$                                         
  $FLTCON NALPHA=5.,ALSCHD(1)=-2.0,0.0,2.0,                                      
   ALSCHD(4)=4.0,8.0,LOOP=2.0$                                                   
  $OPTINS SREF=225.8,CBARR=5.75,BLREF=41.15$                                     
  $SYNTHS XCG=7.08,ZCG=0.0,XW=6.1,ZW=-1.4,ALIW=1.1,XH=20.2,                      
    ZH=0.4,ALIH=0.0,XV=21.3,ZV=0.0,VERTUP=.TRUE.$                                
  $BODY NX=10.0,                                                                 
    X(1)=-4.9,0.0,3.0,6.1,9.1,13.3,20.2,23.5,25.9,                               
    R(1)=0.0,1.0,1.75,2.6,2.6,2.6,2.0,1.0,0.0$                                   
  $WGPLNF CHRDTP=4.0,SSPNE=18.7,SSPN=20.6,CHRDR=7.2,SAVSI=0.0,CHSTAT=0.25,       
    TWISTA=-1.1,SSPNDD=0.0,DHDADI=3.0,DHDADO=3.0,TYPE=1.0$                       
 NACA-W-6-64A412                                                                 
  $HTPLNF CHRDTP=2.3,SSPNE=5.7,SSPN=6.625,CHRDR=0.25,SAVSI=11.0,                 
    CHSTAT=1.0,TWISTA=0.0,TYPE=1.0$                                              
 NACA-H-4-0012                                                                   
  $VTPLNF CHRDTP=2.7,SSPNE=5.0,SSPN=5.2,CHRDR=5.3,SAVSI=31.3,                    
    CHSTAT=0.25,TWISTA=0.0,TYPE=1.0$                                             
 NACA-V-4-0012                                                                   
 CASEID SKYHOGG BODY-WING-HORIZONTAL TAIL-VERTICAL TAIL CONFIG        
 DAMP                                                                            
 NEXT CASE                                                                       
1          THE FOLLOWING IS A LIST OF ALL INPUT CARDS FOR THIS CASE.
0
  $FLTCON NMACH=2.0,MACH(1)=0.1,0.2$                                             
  $FLTCON NALT=2.0,ALT(1)=5000.0,8000.0$                                         
  $FLTCON NALPHA=5.,ALSCHD(1)=-2.0,0.0,2.0,                                      
   ALSCHD(4)=4.0,8.0,LOOP=2.0$                                                   
  $OPTINS SREF=225.8,CBARR=5.75,BLREF=41.15$                                     
  $SYNTHS XCG=7.08,ZCG=0.0,XW=6.1,ZW=-1.4,ALIW=1.1,XH=20.2,                      
    ZH=0.4,ALIH=0.0,XV=21.3,ZV=0.0,VERTUP=.TRUE.$                                
  $BODY NX=10.0,                                                                 
    X(1)=-4.9,0.0,3.0,6.1,9.1,13.3,20.2,23.5,25.9,                               
    R(1)=0.0,1.0,1.75,2.6,2.6,2.6,2.0,1.0,0.0$                                   
  $WGPLNF CHRDTP=4.0,SSPNE=18.7,SSPN=20.6,CHRDR=7.2,SAVSI=0.0,CHSTAT=0.25,       
    TWISTA=-1.1,SSPNDD=0.0,DHDADI=3.0,DHDADO=3.0,TYPE=1.0$                       
 NACA-W-6-64A412                                                                 
  $HTPLNF CHRDTP=2.3,SSPNE=5.7,SSPN=6.625,CHRDR=0.25,SAVSI=11.0,                 
    CHSTAT=1.0,TWISTA=0.0,TYPE=1.0$                                              
 NACA-H-4-0012                                                                   
  $VTPLNF CHRDTP=2.7,SSPNE=5.0,SSPN=5.2,CHRDR=5.3,SAVSI=31.3,                    
    CHSTAT=0.25,TWISTA=0.0,TYPE=1.0$                                             
 NACA-V-4-0012                                                                   
 CASEID SKYHOGG BODY-WING-HORIZONTAL TAIL-VERTICAL TAIL CONFIG        
 DAMP                                                                            
 NEXT CASE                                                                       
0 INPUT DIMENSIONS ARE IN FT, SCALE FACTOR IS 1.0000

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 =  -3.09292 DEG.

                                 IDEAL LIFT COEFFICIENT =   0.40000

                  ZERO LIFT PITCHING MOMENT COEFFICIENT =  -0.08719

                             MACH ZERO LIFT-CURVE-SLOPE =   0.09654 /DEG.

                                    LEADING EDGE RADIUS =   0.00993 FRACTION CHORD

                              MAXIMUM AIRFOIL THICKNESS =   0.12000 FRACTION CHORD

                                                DELTA-Y =   2.46808 PERCENT CHORD


0                         MACH= 0.1000 LIFT-CURVE-SLOPE =   0.09693 /DEG.      XAC =   0.26404
0                         MACH= 0.2000 LIFT-CURVE-SLOPE =   0.09811 /DEG.      XAC =   0.26457
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 =   0.09596 /DEG.

                                    LEADING EDGE RADIUS =   0.01587 FRACTION CHORD

                              MAXIMUM AIRFOIL THICKNESS =   0.12000 FRACTION CHORD

                                                DELTA-Y =   3.16898 PERCENT CHORD


0                         MACH= 0.1000 LIFT-CURVE-SLOPE =   0.09636 /DEG.      XAC =   0.25854
0                         MACH= 0.2000 LIFT-CURVE-SLOPE =   0.09761 /DEG.      XAC =   0.25881
1                             AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM   
                                                    VERTICAL 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 =   0.09596 /DEG.

                                    LEADING EDGE RADIUS =   0.01587 FRACTION CHORD

                              MAXIMUM AIRFOIL THICKNESS =   0.12000 FRACTION CHORD

                                                DELTA-Y =   3.16898 PERCENT CHORD


0                         MACH= 0.1000 LIFT-CURVE-SLOPE =   0.09636 /DEG.      XAC =   0.25854
0                         MACH= 0.2000 LIFT-CURVE-SLOPE =   0.09761 /DEG.      XAC =   0.25881
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
                                 SKYHOGG BODY-WING-HORIZONTAL TAIL-VERTICAL TAIL CONFIG
 
 -----------------------  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 0.100    5000.00     109.70   1.7609E+03     500.843     6.1507E+05           225.800      5.750    41.150     7.080     0.000
0                                                               -------------------DERIVATIVE (PER DEGREE)-------------------
0 ALPHA     CD       CL       CM       CN       CA       XCP        CLA          CMA          CYB          CNB          CLB
0
   -2.0    0.032    0.113   -0.0340   0.112    0.035   -0.304    8.926E-02   -2.105E-02   -3.458E-03    9.142E-04   -6.161E-04
    0.0    0.035    0.296   -0.0752   0.296    0.035   -0.254    9.350E-02   -2.034E-02                             -6.205E-04
    2.0    0.042    0.487   -0.1153   0.488    0.025   -0.236    9.732E-02   -1.971E-02                             -6.268E-04
    4.0    0.052    0.685   -0.1541   0.687    0.004   -0.224    1.005E-01   -1.927E-02                             -6.349E-04
    8.0    0.084    1.098   -0.2304   1.099   -0.069   -0.210    1.059E-01   -1.890E-02                             -6.554E-04
0                                    ALPHA     Q/QINF    EPSLON  D(EPSLON)/D(ALPHA)
0
                                     -2.0      1.000      0.953        0.571
                                      0.0      1.000      2.094        0.583
                                      2.0      1.000      3.284        0.606
                                      4.0      1.000      4.520        0.610
                                      8.0      1.000      6.897        0.594
1                               AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
                                                         DYNAMIC DERIVATIVES
                                        WING-BODY-VERTICAL TAIL-HORIZONTAL TAIL CONFIGURATION
                                 SKYHOGG BODY-WING-HORIZONTAL TAIL-VERTICAL TAIL CONFIG
 
 -----------------------  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 0.100    5000.00     109.70   1.7609E+03     500.843     6.1507E+05           225.800      5.750    41.150     7.080     0.000
                                                    DYNAMIC DERIVATIVES (PER DEGREE)
0           -------PITCHING-------    -----ACCELERATION------    --------------ROLLING--------------    --------YAWING--------
0   ALPHA       CLQ          CMQ           CLAD         CMAD         CLP          CYP          CNP          CNR          CLR
0
    -2.00    9.739E-02   -8.918E-02     1.874E-02   -4.247E-02   -7.824E-03   -1.516E-03   -1.498E-04   -1.059E-03    6.334E-04
     0.00                               1.913E-02   -4.336E-02   -8.226E-03   -1.649E-03   -4.034E-04   -1.068E-03    1.240E-03
     2.00                               1.991E-02   -4.512E-02   -8.599E-03   -1.792E-03   -6.631E-04   -1.073E-03    1.878E-03
     4.00                               2.003E-02   -4.540E-02   -8.890E-03   -1.942E-03   -9.290E-04   -1.073E-03    2.542E-03
     8.00                               1.952E-02   -4.424E-02   -9.387E-03   -2.262E-03   -1.479E-03   -1.060E-03    3.926E-03
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
                                 SKYHOGG BODY-WING-HORIZONTAL TAIL-VERTICAL TAIL CONFIG
 
 -----------------------  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 0.200    5000.00     219.39   1.7609E+03     500.843     1.2301E+06           225.800      5.750    41.150     7.080     0.000
0                                                               -------------------DERIVATIVE (PER DEGREE)-------------------
0 ALPHA     CD       CL       CM       CN       CA       XCP        CLA          CMA          CYB          CNB          CLB
0
   -2.0    0.028    0.114   -0.0335   0.113    0.032   -0.297    9.000E-02   -2.124E-02   -3.465E-03    8.781E-04   -6.226E-04
    0.0    0.031    0.298   -0.0751   0.298    0.031   -0.252    9.421E-02   -2.051E-02                             -6.270E-04
    2.0    0.038    0.491   -0.1155   0.492    0.021   -0.235    9.800E-02   -1.987E-02                             -6.332E-04
    4.0    0.048    0.690   -0.1546   0.692    0.000   -0.223    1.011E-01   -1.943E-02                             -6.413E-04
    8.0    0.081    1.105   -0.2316   1.106   -0.074   -0.209    1.065E-01   -1.906E-02                             -6.614E-04
0                                    ALPHA     Q/QINF    EPSLON  D(EPSLON)/D(ALPHA)
0
                                     -2.0      1.000      0.957        0.573
                                      0.0      1.000      2.103        0.585
                                      2.0      1.000      3.297        0.609
                                      4.0      1.000      4.537        0.612
                                      8.0      1.000      6.923        0.596
1                               AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
                                                         DYNAMIC DERIVATIVES
                                        WING-BODY-VERTICAL TAIL-HORIZONTAL TAIL CONFIGURATION
                                 SKYHOGG BODY-WING-HORIZONTAL TAIL-VERTICAL TAIL CONFIG
 
 -----------------------  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 0.200    5000.00     219.39   1.7609E+03     500.843     1.2301E+06           225.800      5.750    41.150     7.080     0.000
                                                    DYNAMIC DERIVATIVES (PER DEGREE)
0           -------PITCHING-------    -----ACCELERATION------    --------------ROLLING--------------    --------YAWING--------
0   ALPHA       CLQ          CMQ           CLAD         CMAD         CLP          CYP          CNP          CNR          CLR
0
    -2.00    9.840E-02   -8.993E-02     1.900E-02   -4.307E-02   -7.877E-03   -1.525E-03   -1.499E-04   -1.057E-03    6.448E-04
     0.00                               1.940E-02   -4.398E-02   -8.276E-03   -1.659E-03   -4.038E-04   -1.066E-03    1.264E-03
     2.00                               2.018E-02   -4.574E-02   -8.646E-03   -1.802E-03   -6.637E-04   -1.070E-03    1.915E-03
     4.00                               2.030E-02   -4.602E-02   -8.934E-03   -1.953E-03   -9.297E-04   -1.070E-03    2.593E-03
     8.00                               1.978E-02   -4.483E-02   -9.423E-03   -2.273E-03   -1.479E-03   -1.057E-03    4.003E-03
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
                                 SKYHOGG BODY-WING-HORIZONTAL TAIL-VERTICAL TAIL CONFIG
 
 -----------------------  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 0.100    8000.00     108.52   1.5721E+03     490.151     5.6457E+05           225.800      5.750    41.150     7.080     0.000
0                                                               -------------------DERIVATIVE (PER DEGREE)-------------------
0 ALPHA     CD       CL       CM       CN       CA       XCP        CLA          CMA          CYB          CNB          CLB
0
   -2.0    0.032    0.113   -0.0340   0.112    0.036   -0.305    8.926E-02   -2.106E-02   -3.458E-03    9.190E-04   -6.161E-04
    0.0    0.035    0.296   -0.0753   0.296    0.035   -0.254    9.350E-02   -2.034E-02                             -6.205E-04
    2.0    0.042    0.487   -0.1154   0.488    0.025   -0.236    9.732E-02   -1.971E-02                             -6.268E-04
    4.0    0.052    0.685   -0.1541   0.687    0.004   -0.224    1.005E-01   -1.927E-02                             -6.349E-04
    8.0    0.085    1.098   -0.2304   1.099   -0.069   -0.210    1.059E-01   -1.891E-02                             -6.554E-04
0                                    ALPHA     Q/QINF    EPSLON  D(EPSLON)/D(ALPHA)
0
                                     -2.0      1.000      0.953        0.571
                                      0.0      1.000      2.094        0.583
                                      2.0      1.000      3.284        0.606
                                      4.0      1.000      4.520        0.610
                                      8.0      1.000      6.897        0.594
1                               AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
                                                         DYNAMIC DERIVATIVES
                                        WING-BODY-VERTICAL TAIL-HORIZONTAL TAIL CONFIGURATION
                                 SKYHOGG BODY-WING-HORIZONTAL TAIL-VERTICAL TAIL CONFIG
 
 -----------------------  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 0.100    8000.00     108.52   1.5721E+03     490.151     5.6457E+05           225.800      5.750    41.150     7.080     0.000
                                                    DYNAMIC DERIVATIVES (PER DEGREE)
0           -------PITCHING-------    -----ACCELERATION------    --------------ROLLING--------------    --------YAWING--------
0   ALPHA       CLQ          CMQ           CLAD         CMAD         CLP          CYP          CNP          CNR          CLR
0
    -2.00    9.739E-02   -8.918E-02     1.874E-02   -4.247E-02   -7.824E-03   -1.516E-03   -1.498E-04   -1.060E-03    6.334E-04
     0.00                               1.913E-02   -4.336E-02   -8.226E-03   -1.649E-03   -4.034E-04   -1.069E-03    1.240E-03
     2.00                               1.991E-02   -4.512E-02   -8.599E-03   -1.792E-03   -6.631E-04   -1.073E-03    1.878E-03
     4.00                               2.003E-02   -4.540E-02   -8.890E-03   -1.942E-03   -9.290E-04   -1.074E-03    2.542E-03
     8.00                               1.952E-02   -4.424E-02   -9.387E-03   -2.262E-03   -1.479E-03   -1.061E-03    3.926E-03
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
                                 SKYHOGG BODY-WING-HORIZONTAL TAIL-VERTICAL TAIL CONFIG
 
 -----------------------  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 0.200    8000.00     217.04   1.5721E+03     490.151     1.1291E+06           225.800      5.750    41.150     7.080     0.000
0                                                               -------------------DERIVATIVE (PER DEGREE)-------------------
0 ALPHA     CD       CL       CM       CN       CA       XCP        CLA          CMA          CYB          CNB          CLB
0
   -2.0    0.028    0.114   -0.0335   0.113    0.032   -0.297    9.000E-02   -2.124E-02   -3.465E-03    8.829E-04   -6.226E-04
    0.0    0.031    0.298   -0.0751   0.298    0.031   -0.252    9.421E-02   -2.051E-02                             -6.270E-04
    2.0    0.038    0.491   -0.1156   0.492    0.021   -0.235    9.800E-02   -1.987E-02                             -6.332E-04
    4.0    0.049    0.690   -0.1546   0.692    0.000   -0.223    1.011E-01   -1.943E-02                             -6.413E-04
    8.0    0.081    1.105   -0.2316   1.106   -0.073   -0.209    1.065E-01   -1.906E-02                             -6.614E-04
0                                    ALPHA     Q/QINF    EPSLON  D(EPSLON)/D(ALPHA)
0
                                     -2.0      1.000      0.957        0.573
                                      0.0      1.000      2.103        0.585
                                      2.0      1.000      3.297        0.609
                                      4.0      1.000      4.537        0.612
                                      8.0      1.000      6.923        0.596
1                               AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
                                                         DYNAMIC DERIVATIVES
                                        WING-BODY-VERTICAL TAIL-HORIZONTAL TAIL CONFIGURATION
                                 SKYHOGG BODY-WING-HORIZONTAL TAIL-VERTICAL TAIL CONFIG
 
 -----------------------  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 0.200    8000.00     217.04   1.5721E+03     490.151     1.1291E+06           225.800      5.750    41.150     7.080     0.000
                                                    DYNAMIC DERIVATIVES (PER DEGREE)
0           -------PITCHING-------    -----ACCELERATION------    --------------ROLLING--------------    --------YAWING--------
0   ALPHA       CLQ          CMQ           CLAD         CMAD         CLP          CYP          CNP          CNR          CLR
0
    -2.00    9.840E-02   -8.993E-02     1.900E-02   -4.307E-02   -7.877E-03   -1.525E-03   -1.499E-04   -1.057E-03    6.448E-04
     0.00                               1.940E-02   -4.398E-02   -8.276E-03   -1.659E-03   -4.038E-04   -1.066E-03    1.264E-03
     2.00                               2.018E-02   -4.574E-02   -8.646E-03   -1.802E-03   -6.637E-04   -1.071E-03    1.915E-03
     4.00                               2.030E-02   -4.602E-02   -8.934E-03   -1.953E-03   -9.297E-04   -1.071E-03    2.593E-03
     8.00                               1.978E-02   -4.483E-02   -9.424E-03   -2.273E-03   -1.479E-03   -1.057E-03    4.003E-03
1          THE FOLLOWING IS A LIST OF ALL INPUT CARDS FOR THIS CASE.
0
1 END OF JOB.

Импортируйте данные из файлов DATCOM

Используйте функцию datcomimport, чтобы принести Цифровые данные DATCOM в MATLAB.

alldata = datcomimport('astdatcom.out', true, 0);

Исследование импортированных данных DATCOM

Функция datcomimport создает массив ячеек структур, содержащих данные из Цифрового выходного файла DATCOM.

data = alldata{1}
data = 

  struct with fields:

        case: 'SKYHOGG BODY-WING-HORIZONTAL TAIL-VERTICAL TAIL CONFIG'
        mach: [0.1000 0.2000]
         alt: [5000 8000]
       alpha: [-2 0 2 4 8]
       nmach: 2
        nalt: 2
      nalpha: 5
       rnnub: []
      hypers: 0
        loop: 2
        sref: 225.8000
        cbar: 5.7500
       blref: 41.1500
         dim: 'ft'
       deriv: 'deg'
      stmach: 0.6000
      tsmach: 1.4000
        save: 0
       stype: []
        trim: 0
        damp: 1
       build: 1
        part: 0
     highsym: 0
     highasy: 0
     highcon: 0
        tjet: 0
      hypeff: 0
          lb: 0
         pwr: 0
        grnd: 0
       wsspn: 18.7000
       hsspn: 5.7000
      ndelta: 0
       delta: []
      deltal: []
      deltar: []
         ngh: 0
      grndht: []
      config: [1x1 struct]
     version: 1976
          cd: [5x2x2 double]
          cl: [5x2x2 double]
          cm: [5x2x2 double]
          cn: [5x2x2 double]
          ca: [5x2x2 double]
         xcp: [5x2x2 double]
         cma: [5x2x2 double]
         cyb: [5x2x2 double]
         cnb: [5x2x2 double]
         clb: [5x2x2 double]
         cla: [5x2x2 double]
       qqinf: [5x2x2 double]
         eps: [5x2x2 double]
    depsdalp: [5x2x2 double]
         clq: [5x2x2 double]
         cmq: [5x2x2 double]
        clad: [5x2x2 double]
        cmad: [5x2x2 double]
         clp: [5x2x2 double]
         cyp: [5x2x2 double]
         cnp: [5x2x2 double]
         cnr: [5x2x2 double]
         clr: [5x2x2 double]

Заполнение Пропавших без вести данных DATCOM

По умолчанию недостающие точки данных установлены в 99 999, и точки данных установлены в NaN, где никакие методы DATCOM не существуют или где метод не применим.

Это видно в Цифровом выходном файле DATCOM и исследовании импортированных данных это

имейте данные только в первом альфа-значении. Вот импортированные значения данных.

data.cyb
ans(:,:,1) =

   1.0e+04 *

   -0.0000   -0.0000
    9.9999    9.9999
    9.9999    9.9999
    9.9999    9.9999
    9.9999    9.9999


ans(:,:,2) =

   1.0e+04 *

   -0.0000   -0.0000
    9.9999    9.9999
    9.9999    9.9999
    9.9999    9.9999
    9.9999    9.9999

data.cnb
ans(:,:,1) =

   1.0e+04 *

    0.0000    0.0000
    9.9999    9.9999
    9.9999    9.9999
    9.9999    9.9999
    9.9999    9.9999


ans(:,:,2) =

   1.0e+04 *

    0.0000    0.0000
    9.9999    9.9999
    9.9999    9.9999
    9.9999    9.9999
    9.9999    9.9999

data.clq
ans(:,:,1) =

   1.0e+04 *

    0.0000    0.0000
    9.9999    9.9999
    9.9999    9.9999
    9.9999    9.9999
    9.9999    9.9999


ans(:,:,2) =

   1.0e+04 *

    0.0000    0.0000
    9.9999    9.9999
    9.9999    9.9999
    9.9999    9.9999
    9.9999    9.9999

data.cmq
ans(:,:,1) =

   1.0e+04 *

   -0.0000   -0.0000
    9.9999    9.9999
    9.9999    9.9999
    9.9999    9.9999
    9.9999    9.9999


ans(:,:,2) =

   1.0e+04 *

   -0.0000   -0.0000
    9.9999    9.9999
    9.9999    9.9999
    9.9999    9.9999
    9.9999    9.9999

Недостающие точки данных будут заполнены значениями для первой альфы, поскольку эти точки данных предназначаются, чтобы использоваться для всех альфа-значений.

aerotab = {'cyb' 'cnb' 'clq' 'cmq'};

for k = 1:length(aerotab)
    for m = 1:data.nmach
        for h = 1:data.nalt
            data.(aerotab{k})(:,m,h) = data.(aerotab{k})(1,m,h);
        end
    end
end

Вот обновленные импортированные значения данных:

data.cyb
ans(:,:,1) =

   -0.0035   -0.0035
   -0.0035   -0.0035
   -0.0035   -0.0035
   -0.0035   -0.0035
   -0.0035   -0.0035


ans(:,:,2) =

   -0.0035   -0.0035
   -0.0035   -0.0035
   -0.0035   -0.0035
   -0.0035   -0.0035
   -0.0035   -0.0035

data.cnb
ans(:,:,1) =

   1.0e-03 *

    0.9142    0.8781
    0.9142    0.8781
    0.9142    0.8781
    0.9142    0.8781
    0.9142    0.8781


ans(:,:,2) =

   1.0e-03 *

    0.9190    0.8829
    0.9190    0.8829
    0.9190    0.8829
    0.9190    0.8829
    0.9190    0.8829

data.clq
ans(:,:,1) =

    0.0974    0.0984
    0.0974    0.0984
    0.0974    0.0984
    0.0974    0.0984
    0.0974    0.0984


ans(:,:,2) =

    0.0974    0.0984
    0.0974    0.0984
    0.0974    0.0984
    0.0974    0.0984
    0.0974    0.0984

data.cmq
ans(:,:,1) =

   -0.0892   -0.0899
   -0.0892   -0.0899
   -0.0892   -0.0899
   -0.0892   -0.0899
   -0.0892   -0.0899


ans(:,:,2) =

   -0.0892   -0.0899
   -0.0892   -0.0899
   -0.0892   -0.0899
   -0.0892   -0.0899
   -0.0892   -0.0899

Графический вывод аэродинамических коэффициентов

Постройте кривую лифта, перетащите полярные и делающие подачу моменты.

h1 = figure;
figtitle = {'Lift Curve' ''};
for k=1:2
    subplot(2,1,k)
    plot(data.alpha,permute(data.cl(:,k,:),[1 3 2]))
    grid
    ylabel(['Lift Coefficient (Mach =' num2str(data.mach(k)) ')'])
    title(figtitle{k});
end
xlabel('Angle of Attack (deg)')

h2 = figure;
figtitle = {'Drag Polar' ''};
for k=1:2
    subplot(2,1,k)
    plot(permute(data.cd(:,k,:),[1 3 2]),permute(data.cl(:,k,:),[1 3 2]))
    grid
    ylabel(['Lift Coefficient (Mach =' num2str(data.mach(k)) ')'])
    title(figtitle{k})
end
xlabel('Drag Coefficient')

h3 = figure;
figtitle = {'Pitching Moment' ''};
for k=1:2
    subplot(2,1,k)
    plot(permute(data.cm(:,k,:),[1 3 2]),permute(data.cl(:,k,:),[1 3 2]))
    grid
    ylabel(['Lift Coefficient (Mach =' num2str(data.mach(k)) ')'])
    title(figtitle{k})
end
xlabel('Pitching Moment Coefficient')

close(h1,h2,h3);
%#ok<*NOPTS>
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