📄 ex2.out
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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= 1.254E-02
Return to main program from M57O71
1 THE FOLLOWING IS A LIST OF ALL INPUT CARDS FOR THIS CASE.
0
$FLTCON LOOP=3.0$
$WGPLNF TYPE=2.0$
CASEID EXPOSED DOUBLE DELTA WING SOLUTION, EXAMPLE PROBLEM 2, CASE 3
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 DOUBLE DELTA WING SOLUTION, EXAMPLE PROBLEM 2, CASE 3
----------------------- 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 0.015 -0.144 0.0440 -0.145 0.000 -0.304 2.691E-02 -1.000E-02 1.579E-04 5.321E-05 7.648E-04
-4.0 0.008 -0.072 0.0216 -0.072 0.003 -0.299 3.595E-02 -1.189E-02 3.946E-05 1.326E-05 3.824E-04
-2.0 0.005 0.000 -0.0036 0.000 0.005 18.814 3.595E-02 -1.335E-02 0.000E+00 0.000E+00 0.000E+00
0.0 0.008 0.072 -0.0318 0.072 0.008 -0.442 3.595E-02 -1.471E-02 3.946E-05 1.454E-05 -3.824E-04
2.0 0.015 0.144 -0.0624 0.144 0.010 -0.433 3.595E-02 -1.572E-02 1.579E-04 5.784E-05 -7.648E-04
4.0 0.027 0.216 -0.0946 0.217 0.012 -0.436 3.690E-02 -1.653E-02 3.584E-04 1.304E-04 -1.147E-03
8.0 0.068 0.371 -0.1641 0.377 0.015 -0.436 4.117E-02 -1.714E-02 1.072E-03 3.855E-04 -1.973E-03
12.0 0.135 0.545 -0.2318 0.561 0.018 -0.413 4.382E-02 -1.919E-02 2.330E-03 8.207E-04 -2.899E-03
16.0 0.228 0.721 -0.3176 0.756 0.020 -0.420 4.294E-02 -2.257E-02 4.101E-03 1.444E-03 -3.837E-03
20.0 0.346 0.889 -0.4123 0.954 0.022 -0.432 4.030E-02 -2.588E-02 6.256E-03 2.208E-03 -4.726E-03
24.0 0.489 1.044 -0.5246 1.153 0.022 -0.455 3.733E-02 -3.027E-02 8.692E-03 3.091E-03 -5.552E-03
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
WING ALONE CONFIGURATION
EXPOSED DOUBLE DELTA WING SOLUTION, EXAMPLE PROBLEM 2, CASE 3
----------------------- 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 0.020 -0.144 0.0440 -0.145 0.005 -0.303 2.691E-02 -1.000E-02 1.579E-04 5.317E-05 7.648E-04
-4.0 0.013 -0.072 0.0216 -0.073 0.008 -0.298 3.595E-02 -1.189E-02 3.946E-05 1.324E-05 3.824E-04
-2.0 0.011 0.000 -0.0036 0.000 0.011 9.597 3.595E-02 -1.335E-02 0.000E+00 0.000E+00 0.000E+00
0.0 0.013 0.072 -0.0318 0.072 0.013 -0.442 3.595E-02 -1.471E-02 3.946E-05 1.454E-05 -3.824E-04
2.0 0.020 0.144 -0.0624 0.144 0.015 -0.432 3.595E-02 -1.572E-02 1.579E-04 5.782E-05 -7.648E-04
4.0 0.032 0.216 -0.0946 0.217 0.017 -0.435 3.690E-02 -1.653E-02 3.584E-04 1.304E-04 -1.147E-03
8.0 0.073 0.371 -0.1641 0.377 0.020 -0.435 4.117E-02 -1.714E-02 1.072E-03 3.853E-04 -1.973E-03
12.0 0.140 0.545 -0.2318 0.562 0.023 -0.412 4.382E-02 -1.919E-02 2.330E-03 8.203E-04 -2.899E-03
16.0 0.233 0.721 -0.3176 0.758 0.025 -0.419 4.294E-02 -2.257E-02 4.101E-03 1.444E-03 -3.837E-03
20.0 0.352 0.889 -0.4123 0.955 0.027 -0.432 4.030E-02 -2.588E-02 6.256E-03 2.207E-03 -4.726E-03
24.0 0.494 1.044 -0.5246 1.155 0.027 -0.454 3.733E-02 -3.027E-02 8.692E-03 3.089E-03 -5.552E-03
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
WING ALONE CONFIGURATION
EXPOSED DOUBLE DELTA WING SOLUTION, EXAMPLE PROBLEM 2, CASE 3
----------------------- 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** 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 DOUBLE DELTA WING SOLUTION, EXAMPLE PROBLEM 2, CASE 3
----------------------- 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
12.0
16.0
20.0
24.0
0*** NDM PRINTED WHEN NO DATCOM METHODS EXIST
0** CD0= 1.254E-02
Return to main program from M57O71
1 THE FOLLOWING IS A LIST OF ALL INPUT CARDS FOR THIS CASE.
0
1 END OF JOB.
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