📄 ex2.out
字号:
-4.0 0.016 -0.034 0.0178 -0.035 0.014 -0.508 1.748E-02 4.828E-05
-2.0 0.015 0.000 0.0000 -0.001 0.015 0.000 1.703E-02 7.278E-07
0.0 0.016 0.034 -0.0178 0.034 0.016 -0.524 1.748E-02 -4.684E-05
2.0 0.020 0.070 -0.0357 0.071 0.017 -0.506 1.815E-02 -9.702E-05
4.0 0.026 0.107 -0.0535 0.108 0.018 -0.495 1.835E-02 -1.488E-04
8.0 0.046 0.180 -0.0892 0.184 0.020 -0.484 1.770E-02 -2.535E-04
12.0 0.073 0.248 NDM 0.258 0.020 1.611E-02 -3.549E-04
16.0 0.105 0.309 NDM 0.326 0.016 1.427E-02 -4.477E-04
20.0 0.139 0.362 NDM 0.388 0.006 1.325E-02 -5.336E-04
24.0 0.177 0.415 NDM 0.451 -0.007 1.284E-02 -6.198E-04
0*** NDM PRINTED WHEN NO DATCOM METHODS EXIST
Return to main program from M57O71
1 THE FOLLOWING IS A LIST OF ALL INPUT CARDS FOR THIS CASE.
0
$FLTCON NMACH=2.0,MACH=0.6,2.5, LOOP=2.0, NALT=2.0, ALT=0.0, 90000.0$
$SYNTHS XW=2.497, ZW=0.710$
$WGPLNF SSPNOP=1.11, CHRDBP=2.24, CHRDR=4.01,
SAVSI=75.1, SAVSO=55.0, TYPE=3.0$
$WGSCHR TOVC=0.1, LERI=0.011, LERO=0.0138, TOVCO=0.12,
XOVCO=0.40, CMOT=-0.0262$
CASEID EXPOSED CRANKED WING SOLUTION, EXAMPLE PROBLEM 2, CASE 2
SAVE
NEXT CASE
0 INPUT DIMENSIONS ARE IN FT, SCALE FACTOR IS 1.0000
Return to main program from M01O01
0*** WARNING *** WING NOT STRAIGHT TAPERED. UNIFORM SECTION ASSUMED.
Return to main program from M50O62
Return to main program from M02O02
Return to main program from M51O63
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
WING ALONE CONFIGURATION
EXPOSED CRANKED WING SOLUTION, EXAMPLE PROBLEM 2, CASE 2
----------------------- 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 0.00 669.80 2.1162E+03 518.670 4.2409E+06 8.050 2.460 4.280 4.140 0.000
0 -------------------DERIVATIVE (PER DEGREE)-------------------
0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB
0
-6.0 0.010 -0.131 0.0398 -0.132 -0.003 -0.303 3.280E-02 -1.219E-02 1.405E-04 4.424E-05 6.977E-04
-4.0 0.007 -0.066 0.0194 -0.066 0.002 -0.295 3.280E-02 -1.085E-02 3.512E-05 1.100E-05 3.489E-04
-2.0 0.005 0.000 -0.0036 0.000 0.005 18.814 3.280E-02 -1.218E-02 0.000E+00 0.000E+00 0.000E+00
0.0 0.007 0.066 -0.0293 0.066 0.007 -0.447 3.280E-02 -1.342E-02 3.512E-05 1.214E-05 -3.489E-04
2.0 0.010 0.131 -0.0573 0.131 0.006 -0.435 3.280E-02 -1.434E-02 1.405E-04 4.822E-05 -6.977E-04
4.0 0.022 0.197 -0.0866 0.198 0.008 -0.438 3.671E-02 -1.639E-02 3.161E-04 1.087E-04 -1.047E-03
8.0 0.101 0.375 -0.1658 0.385 0.047 -0.430 4.880E-02 -2.034E-02 1.118E-03 3.926E-04 -1.994E-03
12.0 0.161 0.587 -0.2494 0.608 0.035 -0.410 5.341E-02 -2.337E-02 2.701E-03 9.509E-04 -3.123E-03
16.0 0.248 0.802 -0.3528 0.840 0.018 -0.420 5.235E-02 -2.712E-02 5.012E-03 1.786E-03 -4.266E-03
20.0 0.357 1.006 -0.4663 1.067 -0.009 -0.437 4.912E-02 -3.093E-02 7.879E-03 2.838E-03 -5.350E-03
24.0 0.479 1.195 -0.6002 1.287 -0.048 -0.466 4.550E-02 -3.600E-02 1.116E-02 4.080E-03 -6.356E-03
0***NOTE*** CRANKED WING ANALYSIS PERFORMED EVEN THOUGH WING HAS A LOW ASPECT RATIO.
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
WING ALONE CONFIGURATION
EXPOSED CRANKED WING SOLUTION, EXAMPLE PROBLEM 2, CASE 2
----------------------- 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 2.500 0.00 2790.81 2.1162E+03 518.670 1.7671E+07 8.050 2.460 4.280 4.140 0.000
0 -------------------DERIVATIVE (PER DEGREE)-------------------
0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB
0
-6.0 0.010 NDM 0.0402 NDM 0.010 -0.492 2.043E-02 -1.005E-02 NDM NDM NDM
-4.0
-2.0
0.0
2.0
4.0
8.0
12.0
16.0
20.0
24.0
0*** NDM PRINTED WHEN NO DATCOM METHODS EXIST
0***NOTE*** CRANKED WING ANALYSIS PERFORMED EVEN THOUGH WING HAS A LOW ASPECT RATIO.
0** CD0= 1.041E-02
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
WING ALONE CONFIGURATION
EXPOSED CRANKED WING SOLUTION, EXAMPLE PROBLEM 2, CASE 2
----------------------- 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 90000.00 590.50 3.6777E+01 403.136 1.0235E+05 8.050 2.460 4.280 4.140 0.000
0 -------------------DERIVATIVE (PER DEGREE)-------------------
0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB
0
-6.0 0.019 -0.131 0.0398 -0.133 0.006 -0.301 3.280E-02 -1.219E-02 1.405E-04 4.418E-05 6.977E-04
-4.0 0.013 -0.066 0.0194 -0.066 0.008 -0.293 3.280E-02 -1.085E-02 3.512E-05 1.098E-05 3.489E-04
-2.0 0.011 0.000 -0.0036 0.000 0.011 9.597 3.280E-02 -1.218E-02 0.000E+00 0.000E+00 0.000E+00
0.0 0.013 0.066 -0.0293 0.066 0.013 -0.447 3.280E-02 -1.342E-02 3.512E-05 1.214E-05 -3.489E-04
2.0 0.019 0.131 -0.0573 0.132 0.015 -0.434 3.280E-02 -1.434E-02 1.405E-04 4.819E-05 -6.977E-04
4.0 0.036 0.197 -0.0866 0.199 0.022 -0.436 3.671E-02 -1.639E-02 3.161E-04 1.085E-04 -1.047E-03
8.0 0.137 0.375 -0.1658 0.390 0.083 -0.425 4.880E-02 -2.034E-02 1.118E-03 3.913E-04 -1.994E-03
12.0 0.242 0.587 -0.2494 0.625 0.114 -0.399 5.341E-02 -2.337E-02 2.701E-03 9.443E-04 -3.123E-03
16.0 0.395 0.802 -0.3528 0.880 0.158 -0.401 5.235E-02 -2.712E-02 5.012E-03 1.764E-03 -4.266E-03
20.0 0.584 1.006 -0.4663 1.145 0.205 -0.407 4.912E-02 -3.093E-02 7.879E-03 2.785E-03 -5.350E-03
24.0 0.798 1.195 -0.6002 1.416 0.243 -0.424 4.550E-02 -3.600E-02 1.116E-02 3.973E-03 -6.356E-03
0***NOTE*** CRANKED WING ANALYSIS PERFORMED EVEN THOUGH WING HAS A LOW ASPECT RATIO.
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
WING ALONE CONFIGURATION
EXPOSED CRANKED WING SOLUTION, EXAMPLE PROBLEM 2, CASE 2
----------------------- 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 2.500 90000.00 2460.43 3.6777E+01 403.136 4.2644E+05 8.050 2.460 4.280 4.140 0.000
0 -------------------DERIVATIVE (PER DEGREE)-------------------
0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB
0
-6.0 0.013 NDM 0.0402 NDM 0.013 -0.492 2.043E-02 -1.005E-02 NDM NDM NDM
-4.0
-2.0
0.0
2.0
4.0
8.0
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