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DATCOM BODY ALONE CONFIGURATION
CONFIGURATION BUILDUP, EXAMPLE PROBLEM 3, CASE 1
----------------------- 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 4.2600E+06 2.250 0.822 3.000 2.600 0.000
0 -------------------DERIVATIVE (PER DEGREE)-------------------
0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB
0
-2.0 0.008 -0.003 -0.0099 -0.004 0.008 2.735 1.610E-03 5.050E-03 -1.610E-03 -1.384E-03 0.000E+00
0.0 0.008 0.000 0.0000 0.000 0.008 ****** 1.663E-03 4.947E-03 -1.663E-03 -1.355E-03 0.000E+00
2.0 0.008 0.003 0.0099 0.004 0.008 2.735 1.717E-03 4.844E-03 -1.717E-03 -1.327E-03 0.000E+00
4.0 0.009 0.007 0.0194 0.007 0.008 2.597 1.823E-03 4.640E-03 -1.823E-03 -1.271E-03 0.000E+00
8.0 0.010 0.015 0.0371 0.016 0.008 2.338 2.032E-03 4.238E-03 -2.032E-03 -1.161E-03 0.000E+00
12.0 0.013 0.023 0.0533 0.025 0.008 2.103 2.234E-03 3.852E-03 -2.234E-03 -1.055E-03 0.000E+00
16.0 0.017 0.032 0.0679 0.036 0.008 1.890 2.423E-03 3.488E-03 -2.423E-03 -9.556E-04 0.000E+00
20.0 0.023 0.043 0.0812 0.048 0.007 1.700 2.602E-03 3.143E-03 -2.602E-03 -8.613E-04 0.000E+00
24.0 0.030 0.053 0.0931 0.061 0.006 1.530 2.778E-03 2.806E-03 -2.778E-03 -7.689E-04 0.000E+00
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
WING ALONE CONFIGURATION
CONFIGURATION BUILDUP, EXAMPLE PROBLEM 3, CASE 1
----------------------- 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 4.2600E+06 2.250 0.822 3.000 2.600 0.000
0 -------------------DERIVATIVE (PER DEGREE)-------------------
0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB
0
-2.0 0.008 -0.093 0.0150 -0.094 0.005 -0.161 4.643E-02 -7.732E-03 7.482E-06 1.178E-05 4.450E-04
0.0 0.006 0.000 0.0000 0.000 0.006 ****** 4.664E-02 -7.744E-03 0.000E+00 0.000E+00 0.000E+00
2.0 0.008 0.093 -0.0159 0.094 0.005 -0.171 4.672E-02 -8.358E-03 7.483E-06 1.180E-05 -4.450E-04
4.0 0.014 0.187 -0.0334 0.187 0.001 -0.178 4.660E-02 -9.097E-03 3.013E-05 4.744E-05 -8.915E-04
8.0 0.039 0.372 -0.0727 0.374 -0.013 -0.195 4.519E-02 -9.536E-03 1.200E-04 1.884E-04 -1.774E-03
12.0 0.077 0.548 -0.1097 0.552 -0.038 -0.199 3.824E-02 -7.841E-03 2.624E-04 4.103E-04 -2.616E-03
16.0 0.115 0.678 -0.1354 0.683 -0.076 -0.198 2.442E-02 -5.730E-03 4.073E-04 6.265E-04 -3.233E-03
20.0 0.137 0.744 -0.1556 0.746 -0.125 -0.209 7.068E-03 -3.694E-03 5.029E-04 7.562E-04 -3.548E-03
24.0 0.134 0.734 -0.1649 0.725 -0.176 -0.227 -1.181E-02 -9.999E-04 5.102E-04 7.400E-04 -3.503E-03
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
HORIZONTAL TAIL CONFIGURATION
CONFIGURATION BUILDUP, EXAMPLE PROBLEM 3, CASE 1
----------------------- 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 4.2600E+06 2.250 0.822 3.000 2.600 0.000
0 -------------------DERIVATIVE (PER DEGREE)-------------------
0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB
0
-2.0 0.002 -0.016 0.0358 -0.016 0.001 -2.232 8.000E-03 -1.797E-02 2.227E-07 1.217E-06 4.193E-05
0.0 0.001 0.000 0.0000 0.000 0.001 ****** 8.000E-03 -1.786E-02 0.000E+00 0.000E+00 0.000E+00
2.0 0.002 0.016 -0.0356 0.016 0.001 -2.219 8.075E-03 -1.802E-02 2.227E-07 1.215E-06 -4.193E-05
4.0 0.003 0.032 -0.0721 0.032 0.001 -2.222 8.176E-03 -1.841E-02 9.122E-07 4.952E-06 -8.463E-05
8.0 0.009 0.065 -0.1471 0.066 0.000 -2.233 7.953E-03 -1.820E-02 3.758E-06 2.023E-05 -1.709E-04
12.0 0.018 0.096 -0.2177 0.098 -0.002 -2.230 6.713E-03 -1.580E-02 8.279E-06 4.373E-05 -2.514E-04
16.0 0.027 0.119 -0.2735 0.122 -0.006 -2.244 4.508E-03 -1.162E-02 1.307E-05 6.736E-05 -3.116E-04
20.0 0.033 0.132 -0.3107 0.135 -0.014 -2.294 2.598E-03 -8.319E-03 1.672E-05 8.359E-05 -3.458E-04
24.0 0.037 0.140 -0.3400 0.143 -0.023 -2.382 1.263E-03 -6.345E-03 1.881E-05 9.487E-05 -3.661E-04
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
VERTICAL TAIL CONFIGURATION
CONFIGURATION BUILDUP, EXAMPLE PROBLEM 3, CASE 1
----------------------- 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 4.2600E+06 2.250 0.822 3.000 2.600 0.000
0 -------------------DERIVATIVE (PER DEGREE)-------------------
0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB
0
-2.0 0.002 0.000 0.0000 0.000 NDM ****** 0.000E+00 0.000E+00 -1.440E-02 5.713E-03 -1.953E-03
0.0 -1.755E-03
2.0 -1.554E-03
4.0 -1.352E-03
8.0 -9.424E-04
12.0 -5.285E-04
16.0 -1.119E-04
20.0 3.051E-04
24.0 7.207E-04
0*** NDM PRINTED WHEN NO DATCOM METHODS EXIST
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
WING-BODY CONFIGURATION
CONFIGURATION BUILDUP, EXAMPLE PROBLEM 3, CASE 1
----------------------- 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 4.2600E+06 2.250 0.822 3.000 2.600 0.000
0 -------------------DERIVATIVE (PER DEGREE)-------------------
0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB
0
-2.0 0.017 -0.125 0.0032 -0.126 0.012 -0.025 6.258E-02 -1.344E-03 -1.610E-03 -1.845E-03 5.509E-04
0.0 0.015 0.000 0.0000 0.000 0.015 ****** 6.258E-02 -1.857E-03 -5.244E-12
2.0 0.017 0.125 -0.0042 0.126 0.012 -0.034 6.273E-02 -2.638E-03 -5.509E-04
4.0 0.026 0.251 -0.0106 0.252 0.008 -0.042 6.269E-02 -3.666E-03 -1.104E-03
8.0 0.081 0.500 -0.0292 0.507 0.011 -0.058 6.082E-02 -4.558E-03 -2.201E-03
12.0 0.177 0.738 -0.0470 0.758 0.019 -0.062 5.089E-02 -3.117E-03 -3.246E-03
16.0 0.262 0.907 -0.0542 0.944 0.002 -0.057 3.176E-02 -1.415E-03 -3.993E-03
20.0 0.992 -0.0583 9.200E-03 -1.249E-04 -4.364E-03
24.0 0.981 -0.0552 -1.458E-02 1.706E-03 -4.317E-03
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
BODY-HORIZONTAL TAIL CONFIGURATION
CONFIGURATION BUILDUP, EXAMPLE PROBLEM 3, CASE 1
----------------------- 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 4.2600E+06 2.250 0.822 3.000 2.600 0.000
0 -------------------DERIVATIVE (PER DEGREE)-------------------
0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB
0
-2.0 0.010 -0.028 0.0435 -0.028 0.009 -1.559 1.376E-02 -2.179E-02 -1.610E-03 -1.845E-03 2.573E-05
0.0 0.010 0.000 0.0000 0.000 0.010 ****** 1.376E-02 -2.166E-02 -2.037E-12
2.0 0.010 0.028 -0.0432 0.028 0.009 -1.550 1.393E-02 -2.201E-02 -2.573E-05
4.0 0.012 0.056 -0.0880 0.056 0.008 -1.561 1.413E-02 -2.263E-02 -5.208E-05
8.0 0.020 0.112 -0.1802 0.114 0.004 -1.579 1.355E-02 -2.171E-02 -1.052E-04
12.0 0.031 0.164 -0.2618 0.167 -0.003 -1.567 1.144E-02 -1.748E-02 -1.534E-04
16.0 0.045 0.204 -0.3201 0.208 -0.013 -1.536 8.048E-03 -1.072E-02 -1.907E-04
20.0 0.056 0.228 -0.3475 0.234 -0.025 -1.486 5.167E-03 -5.093E-03 -2.136E-04
24.0 0.067 0.245 -0.3608 0.251 -0.038 -1.435 3.261E-03 -1.568E-03 -2.293E-04
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
BODY-VERTICAL TAIL CONFIGURATION
CONFIGURATION BUILDUP, EXAMPLE PROBLEM 3, CASE 1
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