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----------------------- 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 -0.003 -0.0099 -0.004 0.010 2.693 1.610E-03 5.050E-03 -1.601E-02 4.329E-03 -1.953E-03
0.0 0.010 0.000 0.0000 0.000 0.010 ****** 1.663E-03 4.947E-03 -1.755E-03
2.0 0.010 0.003 0.0099 0.004 0.010 2.693 1.717E-03 4.844E-03 -1.554E-03
4.0 0.010 0.007 0.0194 0.008 0.010 2.558 1.823E-03 4.640E-03 -1.352E-03
8.0 0.012 0.015 0.0371 0.016 0.010 2.305 2.032E-03 4.238E-03 -9.424E-04
12.0 0.015 0.023 0.0533 0.026 0.010 2.075 2.234E-03 3.852E-03 -5.285E-04
16.0 0.019 0.032 0.0679 0.036 0.009 1.867 2.423E-03 3.488E-03 -1.119E-04
20.0 0.024 0.043 0.0812 0.048 0.008 1.681 2.602E-03 3.143E-03 3.051E-04
24.0 0.032 0.053 0.0931 0.062 0.007 1.513 2.778E-03 2.806E-03 7.207E-04
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
WING-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 0.018 -0.134 0.0229 -0.134 0.014 -0.170 6.696E-02 -1.116E-02 -1.609E-03 -1.844E-03 5.928E-04
0.0 0.016 0.000 0.0000 0.000 0.016 ****** 6.696E-02 -1.170E-02 -5.244E-12
2.0 0.018 0.134 -0.0239 0.134 0.014 -0.178 6.751E-02 -1.338E-02 -5.928E-04
4.0 0.028 0.270 -0.0535 0.271 0.009 -0.197 6.800E-02 -1.565E-02 -1.189E-03
8.0 0.086 0.542 -0.1228 0.548 0.010 -0.224 6.676E-02 -1.812E-02 -2.372E-03
12.0 0.187 0.804 -0.1985 0.826 0.016 -0.240 5.806E-02 -1.973E-02 -3.497E-03
16.0 0.281 1.006 -0.2806 1.045 -0.007 -0.269 4.049E-02 -2.182E-02 -4.305E-03
20.0 1.128 -0.3731 1.762E-02 -1.977E-02 -4.710E-03
24.0 1.147 -0.4388 -8.122E-03 -1.307E-02 -4.683E-03
0 ALPHA Q/QINF EPSLON D(EPSLON)/D(ALPHA)
0
-2.0 0.946 -1.234 0.617
0.0 0.910 0.000 0.617
2.0 0.946 1.234 0.603
4.0 0.996 2.413 0.572
8.0 1.000 4.565 0.493
12.0 1.000 6.358 0.361
16.0 1.000 7.452 0.162
20.0 1.000 7.650 -0.065
24.0 1.000 6.929 -0.180
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
WING-BODY-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 0.018 -0.125 0.0032 -0.126 0.014 -0.025 6.258E-02 -1.344E-03 -1.601E-02 3.868E-03 -1.402E-03
0.0 0.016 0.000 0.0000 0.000 0.016 ****** 6.258E-02 -1.857E-03 -1.755E-03
2.0 0.018 0.125 -0.0042 0.126 0.014 -0.034 6.273E-02 -2.638E-03 -2.105E-03
4.0 0.027 0.251 -0.0106 0.252 0.010 -0.042 6.269E-02 -3.666E-03 -2.456E-03
8.0 0.083 0.500 -0.0292 0.507 0.012 -0.058 6.082E-02 -4.558E-03 -3.144E-03
12.0 0.178 0.738 -0.0470 0.758 0.021 -0.062 5.089E-02 -3.117E-03 -3.775E-03
16.0 0.263 0.907 -0.0542 0.945 0.003 -0.057 3.176E-02 -1.415E-03 -4.105E-03
20.0 0.992 -0.0583 9.200E-03 -1.249E-04 -4.059E-03
24.0 0.981 -0.0552 -1.458E-02 1.706E-03 -3.596E-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
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 0.020 -0.134 0.0229 -0.135 0.015 -0.170 6.696E-02 -1.116E-02 -1.601E-02 3.869E-03 -1.360E-03
0.0 0.018 0.000 0.0000 0.000 0.018 ****** 6.696E-02 -1.170E-02 -1.755E-03
2.0 0.020 0.134 -0.0239 0.135 0.015 -0.178 6.751E-02 -1.338E-02 -2.147E-03
4.0 0.030 0.270 -0.0535 0.271 0.011 -0.197 6.800E-02 -1.565E-02 -2.541E-03
8.0 0.088 0.542 -0.1228 0.548 0.011 -0.224 6.676E-02 -1.812E-02 -3.315E-03
12.0 0.189 0.804 -0.1985 0.826 0.018 -0.240 5.806E-02 -1.973E-02 -4.026E-03
16.0 0.283 1.006 -0.2806 1.045 -0.005 -0.269 4.049E-02 -2.182E-02 -4.417E-03
20.0 1.128 -0.3731 1.762E-02 -1.977E-02 -4.405E-03
24.0 1.147 -0.4388 -8.122E-03 -1.307E-02 -3.962E-03
0 ALPHA Q/QINF EPSLON D(EPSLON)/D(ALPHA)
0
-2.0 0.946 -1.234 0.617
0.0 0.910 0.000 0.617
2.0 0.946 1.234 0.603
4.0 0.996 2.413 0.572
8.0 1.000 4.565 0.493
12.0 1.000 6.358 0.361
16.0 1.000 7.452 0.162
20.0 1.000 7.650 -0.065
24.0 1.000 6.929 -0.180
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
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 0.800 6.4000E+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 NDM NDM NDM NDM 2.892 1.599E-03 4.625E-03 -1.599E-03 -1.267E-03 0.000E+00
0.0 0.008 0.000E+00
2.0 0.008 0.000E+00
4.0 0.008 0.000E+00
8.0 0.009 0.000E+00
12.0 0.009 0.000E+00
16.0 0.010 0.000E+00
20.0 0.012 0.000E+00
24.0 0.013 0.000E+00
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 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
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