📄 ex6.out
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-2.0 0.016 -0.125 0.0032 -0.126 0.012 -0.026 6.258E-02 -1.352E-03 -1.612E-03 -1.845E-03 5.509E-04
0.0 0.015 0.000 0.0000 0.000 0.015 ****** 6.258E-02 -1.864E-03 -5.244E-12
2.0 0.016 0.125 -0.0042 0.126 0.012 -0.034 6.273E-02 -2.646E-03 -5.509E-04
4.0 0.024 0.251 -0.0106 0.252 0.006 -0.042 6.269E-02 -3.674E-03 -1.104E-03
8.0 0.067 0.500 -0.0293 0.505 -0.003 -0.058 6.082E-02 -4.565E-03 -2.201E-03
12.0 0.149 0.738 -0.0471 0.752 -0.007 -0.063 5.089E-02 -3.125E-03 -3.246E-03
16.0 0.236 0.907 -0.0543 0.937 -0.023 -0.058 3.176E-02 -1.423E-03 -3.993E-03
20.0 0.992 -0.0585 9.201E-03 -1.326E-04 -4.364E-03
24.0 0.981 -0.0554 -1.458E-02 1.698E-03 -4.317E-03
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
CHARACTERISTICS OF HIGH LIFT AND CONTROL DEVICES
WING PLAIN TRAILING-EDGE FLAP CONFIGURATION
PLAIN FLAP AILERON, EXAMPLE PROBLEM 6, 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 ----------YAWING MOMENT COEFFICIENT,CN,DUE TO CONTROL DEFLECTION----------
0(DELTAL-DELTAR)= 7.0 15.0 30.0 45.0 60.0
0ALPHA
0
-2.0 6.236E-05 1.336E-04 2.441E-04 3.106E-04 3.670E-04
0.0 0.000E+00 0.000E+00 0.000E+00 0.000E+00 0.000E+00
2.0 -6.236E-05 -1.336E-04 -2.441E-04 -3.106E-04 -3.670E-04
4.0 -1.249E-04 -2.677E-04 -4.890E-04 -6.223E-04 -7.353E-04
8.0 -2.485E-04 -5.326E-04 -9.728E-04 -1.238E-03 -1.463E-03
12.0 -3.666E-04 -7.855E-04 -1.435E-03 -1.826E-03 -2.158E-03
16.0 -4.530E-04 -9.708E-04 -1.773E-03 -2.257E-03 -2.666E-03
20.0 -4.972E-04 -1.065E-03 -1.946E-03 -2.476E-03 -2.926E-03
24.0 -4.908E-04 -1.052E-03 -1.921E-03 -2.445E-03 -2.889E-03
0
0 DELTAL DELTAR (CL)ROLL
0
5.0 -2.0 2.8633E-03
10.0 -5.0 6.1357E-03
20.0 -10.0 1.1208E-02
30.0 -15.0 1.4262E-02
40.0 -20.0 1.6853E-02
Return to main program from M57O71
1 THE FOLLOWING IS A LIST OF ALL INPUT CARDS FOR THIS CASE.
0
$ASYFLP STYPE=3.0, DELTAD(1)=.0130,.0261,.0380,.0513,.0630,.0750,
DELTAS(1)=.013, .0261, .030, .0513, .0630, .0750,
XSOC(1)=.6900,.6955,.6680,.6438,.6454,.6259,
XSPRME=0.55,
XSOC(1)=0.0357,0.0710,0.0956,0.1102,0.1365,0.1359$
CASEID SPOILER-SLOT-DEFLECTOR ON WING, EXAMPLE PROBLEM 6, CASE 2
NEXT CASE
0 INPUT DIMENSIONS ARE IN FT, SCALE FACTOR IS 1.0000
Return to main program from M01O01
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-BODY CONFIGURATION
SPOILER-SLOT-DEFLECTOR ON WING, EXAMPLE PROBLEM 6, CASE 2
----------------------- 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 0.016 -0.125 0.0032 -0.126 0.012 -0.026 6.258E-02 -1.352E-03 -1.612E-03 -1.845E-03 5.509E-04
0.0 0.015 0.000 0.0000 0.000 0.015 ****** 6.258E-02 -1.864E-03 -5.244E-12
2.0 0.016 0.125 -0.0042 0.126 0.012 -0.034 6.273E-02 -2.646E-03 -5.509E-04
4.0 0.024 0.251 -0.0106 0.252 0.006 -0.042 6.269E-02 -3.674E-03 -1.104E-03
8.0 0.067 0.500 -0.0293 0.505 -0.003 -0.058 6.082E-02 -4.565E-03 -2.201E-03
12.0 0.149 0.738 -0.0471 0.752 -0.007 -0.063 5.089E-02 -3.125E-03 -3.246E-03
16.0 0.236 0.907 -0.0543 0.937 -0.023 -0.058 3.176E-02 -1.423E-03 -3.993E-03
20.0 0.992 -0.0585 9.201E-03 -1.326E-04 -4.364E-03
24.0 0.981 -0.0554 -1.458E-02 1.698E-03 -4.317E-03
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
CHARACTERISTICS OF HIGH LIFT AND CONTROL DEVICES
WING WITH SPOILER-SLOT-DEFLECTOR CONFIGURATION
SPOILER-SLOT-DEFLECTOR ON WING, EXAMPLE PROBLEM 6, CASE 2
----------------------- 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 XS/C HS/C DD/C DS/C (CL)ROLL CN
0
0.0357 0.0000 0.0130 0.0130 3.2568E-04 8.395E-04
0.0710 0.0000 0.0261 0.0261 3.2568E-04 1.685E-03
0.0956 0.0000 0.0380 0.0300 2.4677E-04 1.937E-03
0.1102 0.0000 0.0513 0.0513 3.2568E-04 3.313E-03
0.1365 0.0000 0.0630 0.0630 3.2568E-04 4.068E-03
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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