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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 0.006 NDM NDM NDM NDM -0.225 4.982E-02 -1.123E-02 NDM NDM NDM
0.0 NDM
2.0 NDM
4.0 NDM
8.0 NDM
12.0 NDM
16.0 NDM
20.0 NDM
24.0 NDM
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
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 0.800 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 0.001 NDM NDM NDM NDM -2.232 8.485E-03 -1.894E-02 NDM NDM NDM
0.0 NDM
2.0 NDM
4.0 NDM
8.0 NDM
12.0 NDM
16.0 NDM
20.0 NDM
24.0 NDM
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
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 0.800 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 0.003 0.000 0.0000 0.000 NDM ****** 0.000E+00 0.000E+00 NDM NDM NDM
0.0 NDM
2.0 NDM
4.0 NDM
8.0 NDM
12.0 NDM
16.0 NDM
20.0 NDM
24.0 NDM
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 0.800 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 0.019 -0.129 0.0067 -0.129 0.014 -0.052 6.445E-02 -6.953E-03 -1.599E-03 -1.941E-03 1.097E-03
0.0 0.014 0.000 0.000 0.014 6.445E-02 0.000E+00
2.0 0.019 0.129 0.129 0.014 6.445E-02 -1.097E-03
4.0 0.032 0.258 0.259 0.014 6.445E-02 -2.194E-03
8.0 0.098 0.516 0.524 0.026 6.445E-02 -4.388E-03
12.0 0.182 0.773 0.794 0.018 6.445E-02 -6.581E-03
16.0 0.271 1.031 1.066 -0.024 6.445E-02 -8.775E-03
20.0 1.289 6.445E-02 -1.097E-02
24.0 1.547 6.445E-02 -1.316E-02
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 0.800 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 0.009 -0.027 NDM -0.027 0.008 -1.623 1.342E-02 -2.178E-02 -1.599E-03 -1.941E-03 6.755E-05
0.0 0.000 1.342E-02 0.000E+00
2.0 0.027 1.342E-02 -6.755E-05
4.0 0.054 1.342E-02 -1.351E-04
8.0 0.107 1.342E-02 -2.702E-04
12.0 0.161 1.342E-02 -4.053E-04
16.0 0.215 1.342E-02 -5.404E-04
20.0 0.268 1.342E-02 -6.755E-04
24.0 0.322 1.342E-02 -8.106E-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
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 0.800 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 0.011 NDM NDM NDM NDM 2.892 1.599E-03 4.625E-03 NDM NDM NDM
0.0 0.011 NDM
2.0 0.011 NDM
4.0 0.011 NDM
8.0 0.011 NDM
12.0 0.012 NDM
16.0 0.013 NDM
20.0 0.014 NDM
24.0 0.016 NDM
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-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
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