美元FLTCON NMACH = 2.0马赫(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,循环= 2.0 $ $ OPTINS SREF = 225.8, CBARR = 5.75, BLREF = 41.15 $ $合成器XCG = 7.08, ZCG = 0.0, XW = 6.1, ZW = -1.4, ALIW = 1.1, XH = 20.2, ZH型= 0.4,ALIH = 0.0,十五= 21.3,ZV = 0.0, VERTUP = .TRUE。$ $身体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, = 1.0型naca - w - 6 - 64美元美元a412 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$ nca - 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$ nca - v -4-0012机身-机翼-水平尾-垂直尾配置阻尼下一情况

该软件和任何随附的文档被释放“原样”。美国政府没有任何形式，表达或暗示的保证，关于本软件以及任何随附的文件，包括但不限于特定目的的适销性或适用性的任何保证。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.

=数据结构体字段:案例:“SKYHOGG BODY-WING-HORIZONTAL TAIL-VERTICAL尾配置“马赫:[0.1000 - 0.2000]alt:α(5000 8000):[2 0 2 4 8]nmach: 2 nalt: 2 nalpha: 5 rnnub:[]大卖场:0循环:2 sref: 225.8000 cbar: 5.7500 blref: 41.1500暗淡:“英尺”引出:“度”stmach: 0.6000 tsmach: 1.4000保存:0药栓:[]修剪:0潮湿:1建立:1部分:0 highsym: 0 highasy: 0 highcon: 0 tjet: 0 hypeff: 0磅:0压水式反应堆:0接地:0 wsspn: 18.7000 hsspn: 5.7000 ndelta: 0三角洲:[]deltal: [] deltar:[]已:0 grndht:[]配置:[1 x1 struct]版本:1976 cd: [5 x2x2双重的]cl: [5 x2x2双重的]厘米:[5 x2x2双]的cn: [5 x2x2双]的ca: [5 x2x2双]的xcp: [5 x2x2双重的]cma: [5 x2x2双)的地方:[5x2x2 double] clp: [5x2x2 double] clp: [5x2x2 double] clp: [5x2x2 double] clr: [5x2x2 double] clp: [5x2x2 double] clr: [5x2x2 double] clp: [5x2x2 double] clr: [5x2x2 double] clp: [5x2x2 double] clr: [5x2x2 double] clp: [5x2x2 double] clr: [5x2x2 double] clp: [5x2x2 double] clr: [5x2x2 double] clp: [5x2x2 double] clr: [5x2x2 double] clr: [5x2x2 double] clr: [5x2x2 double]

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 9.9999 9.9999 9.9999 9.9999 9.9999 9.9999 9.9999 9.9999 9.9999 9.9999 9.9999 9.9999

ans (:,: 1) = 1.0 e + 04 * 0.0000 0.0000 9.9999 9.9999 9.9999 9.9999 9.9999 9.9999 9.9999 9.9999 ans (:,: 2) = 1.0 e + 04 * 0.0000 0.0000 9.9999 9.9999 9.9999 9.9999 9.9999 9.9999 9.9999 9.9999

ans (:,: 1) = 1.0 e + 04 * 0.0000 0.0000 9.9999 9.9999 9.9999 9.9999 9.9999 9.9999 9.9999 9.9999 ans (:,: 2) = 1.0 e + 04 * 0.0000 0.0000 9.9999 9.9999 9.9999 9.9999 9.9999 9.9999 9.9999 9.9999

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 9.9999 9.9999 9.9999 9.9999 9.9999 9.9999 9.9999 9.9999 9.9999 9.9999 9.9999 9.9999

Ans (:，: 1) = -0.0035 -0.0035 -0.0035 -0.0035 -0.0035 -0.0035 -0.0035 -0.0035 -0.0035 -0.0035

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 0.9190 0.8829 0.9190 0.8829 0.9190 0.8829 0.9190 0.8829 0.9190 0.8829 0.9190 0.8829 0.9190 0.8829 0.9190 0.8829

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

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