Импорт из ВВС США цифровые файлы DATCOM
В этом примере показано, 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>