📄 ex5.out
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DYN(201)= 1.00000E-30 DYN(202)= 1.00000E-30 DYN(203)= 1.00000E-30 DYN(204)= 1.00000E-30 DYN(205)= 1.00000E-30
DYN(206)= 1.00000E-30 DYN(207)= 1.00000E-30 DYN(208)= 1.00000E-30 DYN(209)= 1.00000E-30 DYN(210)= 1.00000E-30
DYN(211)= 1.00000E-30 DYN(212)= 1.00000E-30 DYN(213)= 1.00000E-30
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
WING-BODY CONFIGURATION
BODY-WING DAMPING DERIVATIVES, EXAMPLE PROBLEM 5, 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 0.016 -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
DYNAMIC DERIVATIVES
WING-BODY CONFIGURATION
BODY-WING DAMPING DERIVATIVES, EXAMPLE PROBLEM 5, 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
DYNAMIC DERIVATIVES (PER DEGREE)
0 -------PITCHING------- -----ACCELERATION------ --------------ROLLING-------------- --------YAWING--------
0 ALPHA CLQ CMQ CLAD CMAD CLP CYP CNP CNR CLR
0
-2.00 4.840E-02 -1.968E-02 NDM NDM -5.150E-03 -4.280E-04 1.791E-05 -7.334E-05 -6.158E-04
0.00 -5.144E-03 0.000E+00 0.000E+00 -6.006E-05 0.000E+00
2.00 -5.158E-03 4.277E-04 -1.763E-05 -7.334E-05 6.158E-04
4.00 -5.163E-03 8.652E-04 -3.909E-05 -1.134E-04 1.234E-03
8.00 -5.076E-03 1.801E-03 -1.169E-04 -2.711E-04 2.454E-03
12.00 -4.421E-03 3.058E-03 -4.068E-04 -5.192E-04 3.620E-03
16.00 -3.008E-03 4.697E-03 -9.953E-04 -7.613E-04 4.473E-03
20.00 -1.163E-03 6.597E-03 -1.715E-03 -9.045E-04 4.909E-03
24.00 9.225E-04 7.512E-03 -1.985E-03 -8.832E-04 4.847E-03
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 CONFIGURATION
BODY-WING DAMPING DERIVATIVES, EXAMPLE PROBLEM 5, 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
BASIC BODY PROPERTIES
WETTED AREA XCG ZCG BASE AREA ZERO LIFT DRAG BASE DRAG FRICTION DRAG PRESSURE DRAG
0.5043E+01 2.60 0.00 0.0598 0.7862E-02 0.1587E-02 0.6275E-02 NA
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 0.640E-02 0.350E-02
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 CONFIGURATION
BODY-WING DAMPING DERIVATIVES, EXAMPLE PROBLEM 5, 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 CLA-B(W)= 9.008E-03 CLA-W(B)= 5.163E-02 K-B(W)= 1.940E-01 K-W(B)= 1.112E+00 XAC/C-B(W)= 6.055E-01
ALPHA IV-B(W) IV-W(H) IV-B(H) GAMMA/ GAMMA/
2*PI*ALPHA*V*R (2*PI*ALPHA*V*R)T
-2.000 0.0000E+00 NA NA 0.0000E+00 NA
0.000 0.0000E+00 NA NA 0.0000E+00 NA
2.000 0.0000E+00 NA NA 0.0000E+00 NA
4.000 0.0000E+00 NA NA 0.0000E+00 NA
8.000 0.0000E+00 NA NA NDM NA
12.000 -0.4968E-01 NA NA 0.4592E+00 NA
16.000 -0.1582E+00 NA NA 0.6247E+00 NA
20.000 -0.2150E+00 NA NA 0.7942E+00 NA
24.000 -0.2302E+00 NA NA 0.8727E+00 NA
DYNAMIC DERIVATIVE INCREMENTALS
CLP(GAMMA=CL=0) =-2.9275E-01 CLP(GAMMA)/CLP (GAMMA=0) = 1.0000E+00 CNP/THETA =-2.4243E-04
CYP/GAMMA = 0.0000E+00 CYP/CL (CL=0) = 5.6448E-01
CLB/GAMMA (CMO/THETA)W (CMO/THETA)H
-0.1399E-03 NA NA
0*** NDM PRINTED WHEN NO DATCOM METHODS EXIST
0*** NA PRINTED WHEN METHOD NOT APPLICABLE
1
Return to main program from M57O71
1 THE FOLLOWING IS A LIST OF ALL INPUT CARDS FOR THIS CASE.
0
$SYMFLP NDELTA=6.0, DELTA(1)=0.,.10,.20,.30,.40,.60, PHETE=.0522,
CHRDFI=.2094, CHRDFO=.1554, SPANFI=0.208, SPANFO=.708, FTYPE=1.0,
CB=.01125, TC=.0225, PHETEP=.0391, NTYPE=1.0$
CASEID PLAIN FLAPS ON WING, EXAMPLE PROBLEM 5, CASE 2
DUMP FCM
NEXT CASE
0ERROR ** FLAP INBOARD SPAN, SPANI = 0.20800E+00, IT IS INSIDE THE BODY AS DEFINED BY SSPN AND SSPNE
SPANI IS REDEFINED, SPANI = SSPN-SSPNE = 0.21000E+00
0 INPUT DIMENSIONS ARE IN FT, SCALE FACTOR IS 1.0000
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