📄 ex3.out
字号:
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 0.015 NDM NDM NDM NDM 0.020 6.844E-02 1.365E-03 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 ALPHA Q/QINF EPSLON D(EPSLON)/D(ALPHA)
0
-2.0 0.915 0.000 0.631
0.0
2.0
4.0
8.0
12.0
16.0
20.0
24.0
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-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 0.021 -0.129 NDM -0.130 0.017 -0.108 6.445E-02 -6.953E-03 -1.599E-03 -1.941E-03 NDM
0.0 0.016 0.000 NDM 0.000 0.016 6.445E-02 NDM
2.0 0.021 0.129 NDM 0.130 0.017 6.445E-02 NDM
4.0 0.034 0.258 NDM 0.260 0.016 6.445E-02 NDM
8.0 0.101 0.516 NDM 0.525 0.028 6.445E-02 NDM
12.0 0.185 0.773 NDM 0.795 0.020 6.445E-02 NDM
16.0 0.274 1.031 NDM 1.067 -0.021 6.445E-02 NDM
20.0 1.289 NDM 6.445E-02 NDM
24.0 1.547 NDM 6.445E-02 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-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 0.800 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 0.017 NDM NDM NDM NDM 0.020 6.844E-02 1.365E-03 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 ALPHA Q/QINF EPSLON D(EPSLON)/D(ALPHA)
0
-2.0 0.915 0.000 0.631
0.0
2.0
4.0
8.0
12.0
16.0
20.0
24.0
0*** NDM PRINTED WHEN NO DATCOM METHODS EXIST
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
CONFIGURATION AUXILIARY AND PARTIAL OUTPUT
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 0.800 6.4000E+06 2.250 0.822 3.000 2.600 0.000
BASIC BODY PROPERTIES
WETTED AREA XCG ZCG BASE AREA ZERO LIFT DRAG BASE DRAG FRICTION DRAG PRESSURE DRAG
0.5035E+01 2.60 0.00 0.0698 0.8015E-02 0.2129E-02 0.5487E-02 0.3992E-03
XCG RELATIVE TO THEORETICAL LEADING EDGE MAC= 0.20
BASIC PLANFORM PROPERTIES
TAPER ASPECT QUARTER CHORD QUARTER CHORD ZERO LIFT FRICTION
AREA RATIO RATIO SWEEP MAC X(MAC) Y(MAC) DRAG COEFFICIENT
0 WING
TOTAL THEORITICAL
+ 0.2259E+01 0.298 0.3984E+01 45.000 0.826E+00 0.260E+01 0.615E+00
TOTAL EXPOSED
+ 0.1796E+01 0.331 0.3707E+01 45.000 0.755E+00 0.274E+01 0.747E+00 0.554E-02 0.335E-02
0 HORIZONTAL TAIL
TOTAL THEORITICAL
+ 0.4509E+00 0.602 0.3982E+01 45.000 0.343E+00 0.434E+01 0.307E+00
TOTAL EXPOSED
+ 0.3305E+00 0.661 0.3272E+01 45.000 0.322E+00 0.443E+01 0.392E+00 0.123E-02 0.391E-02
0 VERTICAL TAIL
THEORITICAL INBOARD
+ 0.1223E+01 0.412 0.2358E+01 28.100 0.762E+00 0.379E+01 0.366E+00
EXPOSED INBOARD
+ 0.4048E+00 0.485 0.9804E+00 28.100 0.668E+00 0.386E+01 0.498E+00 NA
OUTBOARD
+ 0.4200E-30 1.000 0.5000E+00 0.000 0.420E+00 0.344E+01 0.630E+00 NA
TOTAL THEORITICAL
+ 0.6113E+00 0.412 0.1179E+01 66.960 0.762E+00 0.379E+01 0.366E+00
TOTAL EXPOSED
+ 0.4048E+00 0.485 0.9804E+00 28.100 0.668E+00 0.386E+01 0.498E+00 NA NA
0*** NA PRINTED WHEN METHOD NOT APPLICABLE
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
CONFIGURATION AUXILIARY AND PARTIAL OUTPUT
WING-BODY-VERTICAL TAIL-HORIZONTAL TAIL CONFIGURATION
CONFIGURATION BUILDUP, EXAMPLE PROBLEM 3, CASE 1
----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------
MACH ALTITUDE VELOCITY ⌨️ 快捷键说明
复制代码
Ctrl + C
搜索代码
Ctrl + F
全屏模式
F11
切换主题
Ctrl + Shift + D
显示快捷键
?
增大字号
Ctrl + =
减小字号
Ctrl + -