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From: Meagan on 28 Jul 2010 12:44
Hi all,

I am currently working on a project that requires me to import USAF Digital Datcom output files into MATLAB data structures using the Aerospace Toolbox. My Datcom output file is:

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****************************************************
* USAF STABILITY AND CONTROL DIGITAL DATCOM *
* PROGRAM REV. JAN 96 DIRECT INQUIRIES TO: *
* WRIGHT LABORATORY (WL/FIGC) ATTN: W. BLAKE *
* WRIGHT PATTERSON AFB, OHIO 45433 *
* PHONE (513) 255-6764, FAX (513) 258-4054 *
****************************************************
1 CONERR - INPUT ERROR CHECKING
0 ERROR CODES - N* DENOTES THE NUMBER OF OCCURENCES OF EACH ERROR
0 A - UNKNOWN VARIABLE NAME
0 B - MISSING EQUAL SIGN FOLLOWING VARIABLE NAME
0 C - NON-ARRAY VARIABLE HAS AN ARRAY ELEMENT DESIGNATION - (N)
0 D - NON-ARRAY VARIABLE HAS MULTIPLE VALUES ASSIGNED
0 E - ASSIGNED VALUES EXCEED ARRAY DIMENSION
0 F - SYNTAX ERROR

0****************************** INPUT DATA CARDS ******************************

$FLTCON NMACH=4.0,MACH(1)=0.1,0.2,0.3,0.35$
$FLTCON NALT=8.0,ALT(1)=1000.0,3000.0,5000.0,7000.0,9000.0,
11000.0,13000.0,15000.0$
$FLTCON NALPHA=10.,ALSCHD(1)=-16.0,-12.0,-8.0,-4.0,-2.0,0.0,2.0,
ALSCHD(8)=4.0,8.0,12.0,LOOP=2.0$
$OPTINS SREF=225.8,CBARR=5.75,BLREF=41.15$
$SYNTHS XCG=7.9,ZCG=-1.4,XW=6.1,ZW=0.0,ALIW=1.1,XH=20.2,
ZH=0.4,ALIH=0.0,XV=21.3,ZV=0.0,VERTUP=.TRUE.$
$BODY NX=10.0,
X(1)=-4.9,0.0,3.0,6.1,9.1,13.3,20.2,23.5,25.9,
R(1)=0.0,1.0,1.75,2.6,2.6,2.6,2.0,1.0,0.0$
$WGPLNF CHRDTP=4.0,SSPNE=18.7,SSPN=20.6,CHRDR=7.2,SAVSI=0.0,CHSTAT=0.25,
TWISTA=-1.1,SSPNDD=0.0,DHDADI=3.0,DHDADO=3.0,TYPE=1.0$
$HTPLNF CHRDTP=2.3,SSPNE=5.7,SSPN=6.625,CHRDR=0.25,SAVSI=11.0,CHSTAT=1.0,
TWISTA=0.0,TYPE=1.0$
$VTPLNF CHRDTP=2.7,SSPNE=5.0,SSPN=5.2,CHRDR=5.3,SAVSI=31.3,
CHSTAT=0.25,TWISTA=0.0,TYPE=1.0$
$SYMFLP NDELTA=5.0,DELTA(1)=-20.0,-10.0,0.0,10.0,20.0,PHETE=0.0522,
CHRDFI=1.3,
CHRDFO=1.3,SPANFI=.1,SPANFO=6.0,FTYPE=1.0,CB=1.3,TC=0.0225,
PHETEP=.0391,NTYPE=1.0$
NACA-W-4-0012
NACA-H-4-0012
NACA-V-4-0012
CASEID SKYHOGG BODY-WING-HORIZONTAL TAIL-VERTICAL TAIL CONFIG
DAMP
NEXT CASE
1 THE FOLLOWING IS A LIST OF ALL INPUT CARDS FOR THIS CASE.
0
$FLTCON NMACH=4.0,MACH(1)=0.1,0.2,0.3,0.35$
$FLTCON NALT=8.0,ALT(1)=1000.0,3000.0,5000.0,7000.0,9000.0,
11000.0,13000.0,15000.0$
$FLTCON NALPHA=10.,ALSCHD(1)=-16.0,-12.0,-8.0,-4.0,-2.0,0.0,2.0,
ALSCHD(8)=4.0,8.0,12.0,LOOP=2.0$
$OPTINS SREF=225.8,CBARR=5.75,BLREF=41.15$
$SYNTHS XCG=7.9,ZCG=-1.4,XW=6.1,ZW=0.0,ALIW=1.1,XH=20.2,
ZH=0.4,ALIH=0.0,XV=21.3,ZV=0.0,VERTUP=.TRUE.$
$BODY NX=10.0,
X(1)=-4.9,0.0,3.0,6.1,9.1,13.3,20.2,23.5,25.9,
R(1)=0.0,1.0,1.75,2.6,2.6,2.6,2.0,1.0,0.0$
$WGPLNF CHRDTP=4.0,SSPNE=18.7,SSPN=20.6,CHRDR=7.2,SAVSI=0.0,CHSTAT=0.25,
TWISTA=-1.1,SSPNDD=0.0,DHDADI=3.0,DHDADO=3.0,TYPE=1.0$
$HTPLNF CHRDTP=2.3,SSPNE=5.7,SSPN=6.625,CHRDR=0.25,SAVSI=11.0,CHSTAT=1.0,
TWISTA=0.0,TYPE=1.0$
$VTPLNF CHRDTP=2.7,SSPNE=5.0,SSPN=5.2,CHRDR=5.3,SAVSI=31.3,
CHSTAT=0.25,TWISTA=0.0,TYPE=1.0$
$SYMFLP NDELTA=5.0,DELTA(1)=-20.0,-10.0,0.0,10.0,20.0,PHETE=0.0522,
CHRDFI=1.3,
CHRDFO=1.3,SPANFI=.1,SPANFO=6.0,FTYPE=1.0,CB=1.3,TC=0.0225,
PHETEP=.0391,NTYPE=1.0$
NACA-W-4-0012
NACA-H-4-0012
NACA-V-4-0012
CASEID SKYHOGG BODY-WING-HORIZONTAL TAIL-VERTICAL TAIL CONFIG
DAMP
NEXT CASE
0ERROR ** FLAP INBOARD SPAN, SPANI = 0.10000E+00, IT IS INSIDE THE BODY AS DEFINED BY SSPN AND SSPNE
SPANI IS REDEFINED, SPANI = SSPN-SSPNE = 0.92500E+00

0 INPUT DIMENSIONS ARE IN FT, SCALE FACTOR IS 1.0000

1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
WING SECTION DEFINITION
0 IDEAL ANGLE OF ATTACK = 0.00000 DEG.

ZERO LIFT ANGLE OF ATTACK = 0.00000 DEG.

IDEAL LIFT COEFFICIENT = 0.00000

ZERO LIFT PITCHING MOMENT COEFFICIENT = 0.00000

MACH ZERO LIFT-CURVE-SLOPE = 0.09596 /DEG.

LEADING EDGE RADIUS = 0.01587 FRACTION CHORD

MAXIMUM AIRFOIL THICKNESS = 0.12000 FRACTION CHORD

DELTA-Y = 3.16898 PERCENT CHORD


0 MACH= 0.1000 LIFT-CURVE-SLOPE = 0.09636 /DEG. XAC = 0.25854
0 MACH= 0.2000 LIFT-CURVE-SLOPE = 0.09761 /DEG. XAC = 0.25881
0 MACH= 0.3000 LIFT-CURVE-SLOPE = 0.09985 /DEG. XAC = 0.25927
0 MACH= 0.3500 LIFT-CURVE-SLOPE = 0.10141 /DEG. XAC = 0.25956
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
HORIZONTAL TAIL SECTION DEFINITION
0 IDEAL ANGLE OF ATTACK = 0.00000 DEG.

ZERO LIFT ANGLE OF ATTACK = 0.00000 DEG.

IDEAL LIFT COEFFICIENT = 0.00000

ZERO LIFT PITCHING MOMENT COEFFICIENT = 0.00000

MACH ZERO LIFT-CURVE-SLOPE = 0.09596 /DEG.

LEADING EDGE RADIUS = 0.01587 FRACTION CHORD

MAXIMUM AIRFOIL THICKNESS = 0.12000 FRACTION CHORD

DELTA-Y = 3.16898 PERCENT CHORD


0 MACH= 0.1000 LIFT-CURVE-SLOPE = 0.09636 /DEG. XAC = 0.25854
0 MACH= 0.2000 LIFT-CURVE-SLOPE = 0.09761 /DEG. XAC = 0.25881
0 MACH= 0.3000 LIFT-CURVE-SLOPE = 0.09985 /DEG. XAC = 0.25927
0 MACH= 0.3500 LIFT-CURVE-SLOPE = 0.10141 /DEG. XAC = 0.25956
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
VERTICAL TAIL SECTION DEFINITION
0 IDEAL ANGLE OF ATTACK = 0.00000 DEG.

ZERO LIFT ANGLE OF ATTACK = 0.00000 DEG.

IDEAL LIFT COEFFICIENT = 0.00000

ZERO LIFT PITCHING MOMENT COEFFICIENT = 0.00000

MACH ZERO LIFT-CURVE-SLOPE = 0.09596 /DEG.

LEADING EDGE RADIUS = 0.01587 FRACTION CHORD

MAXIMUM AIRFOIL THICKNESS = 0.12000 FRACTION CHORD

DELTA-Y = 3.16898 PERCENT CHORD


0 MACH= 0.1000 LIFT-CURVE-SLOPE = 0.09636 /DEG. XAC = 0.25854
0 MACH= 0.2000 LIFT-CURVE-SLOPE = 0.09761 /DEG. XAC = 0.25881
0 MACH= 0.3000 LIFT-CURVE-SLOPE = 0.09985 /DEG. XAC = 0.25927
0 MACH= 0.3500 LIFT-CURVE-SLOPE = 0.10141 /DEG. XAC = 0.25956
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
SKYHOGG BODY-WING-HORIZONTAL TAIL-VERTICAL TAIL CONFIG

----------------------- 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 0.100 1000.00 111.25 2.0409E+03 515.104 6.8768E+05 225.800 5.750 41.150 7.900 -1.400
0 -------------------DERIVATIVE (PER DEGREE)-------------------
0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB
0
-16.0 0.118 -1.415 0.0769 -1.393 -0.276 -0.055 7.394E-02 5.700E-03 -3.114E-03 7.229E-04 -8.974E-04
-12.0 0.082 -1.085 0.0661 -1.078 -0.146 -0.061 9.077E-02 -2.993E-03 -9.139E-04
-8.0 0.051 -0.689 0.0529 -0.690 -0.046 -0.077 9.686E-02 -4.041E-03 -9.475E-04
-4.0 0.034 -0.310 0.0337 -0.311 0.013 -0.108 9.137E-02 -5.591E-03 -9.752E-04
-2.0 0.031 -0.130 0.0218 -0.131 0.026 -0.166 8.761E-02 -6.571E-03 -9.857E-04
0.0 0.030 0.041 0.0075 0.041 0.030 0.183 8.664E-02 -7.626E-03 -9.936E-04
2.0 0.033 0.216 -0.0087 0.217 0.025 -0.040 8.947E-02 -8.265E-03 -1.002E-03
4.0 0.038 0.399 -0.0256 0.400 0.010 -0.064 9.264E-02 -8.663E-03 -1.013E-03
8.0 0.058 0.780 -0.0621 0.781 -0.052 -0.080 9.765E-02 -1.205E-02 -1.038E-03
12.0 0.093 1.180 -0.1220 1.173 -0.155 -0.104 1.022E-01 -1.788E-02 -1.066E-03
0 ALPHA Q/QINF EPSLON D(EPSLON)/D(ALPHA)
0
-16.0 1.000 -8.375 0.493
-12.0 1.000 -6.403 0.527
-8.0 1.000 -4.161 0.565
-4.0 1.000 -1.885 0.568
-2.0 1.000 -0.750 0.560
0.0 1.000 0.353 0.551
2.0 1.000 1.455 0.552
4.0 0.950 2.563 0.554
8.0 0.856 4.779 0.548
12.0 0.989 6.947 0.542
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
DYNAMIC DERIVATIVES
WING-BODY-VERTICAL TAIL-HORIZONTAL TAIL CONFIGURATION
SKYHOGG BODY-WING-HORIZONTAL TAIL-VERTICAL TAIL CONFIG

----------------------- 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 0.100 1000.00 111.25 2.0409E+03 515.104 6.8768E+05 225.800 5.750 41.150 7.900 -1.400
DYNAMIC DERIVATIVES (PER DEGREE)
0 -------PITCHING------- -----ACCELERATION------ --------------ROLLING-------------- --------YAWING--------
0 ALPHA CLQ CMQ CLAD CMAD CLP CYP CNP CNR CLR
0
-16.00 7.120E-02 -7.387E-02 1.516E-02 -3.220E-02 -6.938E-03 -8.811E-05 1.956E-03 -1.097E-03 -4.582E-03
-12.00 1.621E-02 -3.442E-02 -8.527E-03 -3.591E-04 1.459E-03 -9.889E-04 -3.478E-03
-8.00 1.738E-02 -3.691E-02 -9.090E-03 -7.070E-04 9.013E-04 -8.970E-04 -2.132E-03
-4.00 1.748E-02 -3.713E-02 -8.504E-03 -1.017E-03 4.067E-04 -8.626E-04 -8.532E-04
-2.00 1.722E-02 -3.657E-02 -8.127E-03 -1.159E-03 1.662E-04 -8.644E-04 -2.541E-04
0.00 1.696E-02 -3.601E-02 -8.042E-03 -1.292E-03 -6.911E-05 -8.767E-04 3.147E-04
2.00 1.699E-02 -3.609E-02 -8.345E-03 -1.430E-03 -3.095E-04 -8.989E-04 9.001E-04
4.00 1.620E-02 -3.441E-02 -8.677E-03 -1.575E-03 -5.556E-04 -9.325E-04 1.513E-03
8.00 1.444E-02 -3.066E-02 -9.104E-03 -1.886E-03 -1.066E-03 -1.039E-03 2.802E-03
12.00 1.649E-02 -3.502E-02 -9.403E-03 -2.209E-03 -1.589E-03 -1.200E-03 4.127E-03
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
CHARACTERISTICS OF HIGH LIFT AND CONTROL DEVICES
TAIL PLAIN TRAILING-EDGE FLAP CONFIGURATION
SKYHOGG BODY-WING-HORIZONTAL TAIL-VERTICAL TAIL CONFIG
----------------------- 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 0.100 1000.00 111.25 2.0409E+03 515.104 6.8768E+05 225.800 5.750 41.150 7.900 -1.400
0 ---------INCREMENTS DUE TO DEFLECTION--------- ---DERIVATIVES (PER DEGREE)---
0 DELTA D(CL) D(CM) D(CL MAX) D(CD MIN) (CLA)D (CH)A (CH)D


-20.0 -0.051 0.0967 0.046 0.00422 NDM 2.532E-02 3.662E-02
-10.0 -0.037 0.0691 0.027 0.00156 NDM 3.561E-02
0.0 0.000 -0.0001 0.000 0.00000 NDM 3.561E-02
10.0 0.037 -0.0691 0.027 0.00156 NDM 3.561E-02
20.0 0.051 -0.0967 0.046 0.00422 NDM 3.662E-02
0 *** NOTE * HINGE MOMENT DERIVATIVES ARE BASED ON TWICE THE AREA-MOMENT OF THE CONTROL ABOUT ITS HINGE LINE

0 --------- INDUCED DRAG COEFFICIENT INCREMENT , D(CDI) , DUE TO DEFLECTION ---------
0 DELTA = -20.0 -10.0 0.0 10.0 20.0
ALPHA
0
-16.0 4.40E-03 2.80E-03 -1.86E-06 -9.32E-04 -7.90E-04
-12.0 3.75E-03 2.33E-03 -1.40E-06 -4.64E-04 -1.38E-04
-8.0 3.18E-03 1.92E-03 -9.90E-07 -5.79E-05 4.26E-04
-4.0 2.63E-03 1.53E-03 -5.92E-07 3.40E-04 9.79E-04
-2.0 2.35E-03 1.33E-03 -3.93E-07 5.40E-04 1.26E-03
0.0 2.06E-03 1.12E-03 -1.86E-07 7.47E-04 1.54E-03
2.0 1.77E-03 9.12E-04 2.19E-08 9.54E-04 1.83E-03
4.0 1.49E-03 7.07E-04 2.28E-07 1.16E-03 2.12E-03
8.0 9.16E-04 2.95E-04 6.40E-07 1.57E-03 2.69E-03
12.0 3.28E-04 -1.28E-04 1.06E-06 2.00E-03 3.28E-03
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
SKYHOGG BODY-WING-HORIZONTAL TAIL-VERTICAL TAIL CONFIG

----------------------- 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 0.200 1000.00 222.50 2.0409E+03 515.104 1.3754E+06 225.800 5.750 41.150 7.900 -1.400
0 -------------------DERIVATIVE (PER DEGREE)-------------------
0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB
0
-16.0 0.115 -1.421 0.0775 -1.398 -0.281 -0.055 7.297E-02 5.546E-03 -3.120E-03 6.855E-04 -9.055E-04
-12.0 0.078 -1.092 0.0663 -1.085 -0.150 -0.061 9.081E-02 -3.060E-03 -9.208E-04
-8.0 0.047 -0.695 0.0530 -0.694 -0.050 -0.076 9.748E-02 -4.074E-03 -9.542E-04
-4.0 0.031 -0.312 0.0337 -0.314 0.009 -0.108 9.209E-02 -5.629E-03 -9.818E-04
-2.0 0.027 -0.132 0.0217 -0.132 0.023 -0.164 8.837E-02 -6.614E-03 -9.922E-04
0.0 0.027 0.041 0.0073 0.041 0.027 0.177 8.741E-02 -7.679E-03 -1.000E-03
2.0 0.029 0.218 -0.0090 0.219 0.021 -0.041 9.025E-02 -8.388E-03 -1.009E-03
4.0 0.034 0.402 -0.0263 0.404 0.006 -0.065 9.339E-02 -8.827E-03 -1.019E-03
8.0 0.054 0.786 -0.0632 0.786 -0.056 -0.080 9.800E-02 -1.215E-02 -1.044E-03
12.0 0.089 1.186 -0.1235 1.179 -0.159 -0.105 1.019E-01 -1.797E-02 -1.071E-03
0 ALPHA Q/QINF EPSLON D(EPSLON)/D(ALPHA)
0
-16.0 1.000 -8.392 0.491
-12.0 1.000 -6.426 0.527
-8.0 1.000 -4.178 0.567
-4.0 1.000 -1.893 0.570
-2.0 1.000 -0.753 0.562
0.0 1.000 0.355 0.553
2.0 1.000 1.461 0.555
4.0 0.961 2.574 0.556
8.0 0.865 4.798 0.549
12.0 0.994 6.965 0.542
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
DYNAMIC DERIVATIVES
WING-BODY-VERTICAL TAIL-HORIZONTAL TAIL CONFIGURATION
SKYHOGG BODY-WING-HORIZONTAL TAIL-VERTICAL TAIL CONFIG

----------------------- 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 0.200 1000.00 222.50 2.0409E+03 515.104 1.3754E+06 225.800 5.750 41.150 7.900 -1.400
DYNAMIC DERIVATIVES (PER DEGREE)
0 -------PITCHING------- -----ACCELERATION------ --------------ROLLING-------------- --------YAWING--------
0 ALPHA CLQ CMQ CLAD CMAD CLP CYP CNP CNR CLR
0
-16.00 7.195E-02 -7.453E-02 1.527E-02 -3.244E-02 -6.821E-03 -9.622E-05 1.959E-03 -1.096E-03 -4.660E-03
-12.00 1.637E-02 -3.477E-02 -8.508E-03 -3.638E-04 1.463E-03 -9.889E-04 -3.550E-03
-8.00 1.761E-02 -3.740E-02 -9.125E-03 -7.131E-04 9.026E-04 -8.955E-04 -2.179E-03
-4.00 1.773E-02 -3.766E-02 -8.549E-03 -1.025E-03 4.075E-04 -8.602E-04 -8.743E-04
-2.00 1.747E-02 -3.710E-02 -8.178E-03 -1.168E-03 1.666E-04 -8.618E-04 -2.624E-04
0.00 1.720E-02 -3.653E-02 -8.093E-03 -1.301E-03 -6.925E-05 -8.741E-04 3.193E-04
2.00 1.724E-02 -3.662E-02 -8.393E-03 -1.440E-03 -3.101E-04 -8.965E-04 9.175E-04
4.00 1.662E-02 -3.531E-02 -8.719E-03 -1.586E-03 -5.565E-04 -9.304E-04 1.544E-03
8.00 1.475E-02 -3.133E-02 -9.110E-03 -1.897E-03 -1.068E-03 -1.038E-03 2.857E-03
12.00 1.674E-02 -3.556E-02 -9.347E-03 -2.219E-03 -1.590E-03 -1.200E-03 4.199E-03
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
CHARACTERISTICS OF HIGH LIFT AND CONTROL DEVICES
TAIL PLAIN TRAILING-EDGE FLAP CONFIGURATION
SKYHOGG BODY-WING-HORIZONTAL TAIL-VERTICAL TAIL CONFIG
----------------------- 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 0.200 1000.00 222.50 2.0409E+03 515.104 1.3754E+06 225.800 5.750 41.150 7.900 -1.400
0 ---------INCREMENTS DUE TO DEFLECTION--------- ---DERIVATIVES (PER DEGREE)---
0 DELTA D(CL) D(CM) D(CL MAX) D(CD MIN) (CLA)D (CH)A (CH)D


-20.0 -0.052 0.0999 0.046 0.00424 NDM 2.574E-02 3.811E-02
-10.0 -0.038 0.0715 0.027 0.00157 NDM 3.706E-02
0.0 0.000 -0.0001 0.000 0.00000 NDM 3.706E-02
10.0 0.038 -0.0715 0.027 0.00157 NDM 3.706E-02
20.0 0.052 -0.1000 0.046 0.00424 NDM 3.811E-02
0 *** NOTE * HINGE MOMENT DERIVATIVES ARE BASED ON TWICE THE AREA-MOMENT OF THE CONTROL ABOUT ITS HINGE LINE

0 --------- INDUCED DRAG COEFFICIENT INCREMENT , D(CDI) , DUE TO DEFLECTION ---------
0 DELTA = -20.0 -10.0 0.0 10.0 20.0
ALPHA
0
-16.0 4.61E-03 2.93E-03 -1.94E-06 -9.44E-04 -7.75E-04
-12.0 3.93E-03 2.44E-03 -1.45E-06 -4.56E-04 -9.54E-05
-8.0 3.35E-03 2.02E-03 -1.03E-06 -3.50E-05 4.89E-04
-4.0 2.77E-03 1.61E-03 -6.14E-07 3.77E-04 1.06E-03
-2.0 2.49E-03 1.40E-03 -4.08E-07 5.84E-04 1.35E-03
0.0 2.19E-03 1.19E-03 -1.93E-07 7.98E-04 1.65E-03
2.0 1.89E-03 9.72E-04 2.13E-08 1.01E-03 1.95E-03
4.0 1.59E-03 7.59E-04 2.34E-07 1.23E-03 2.24E-03
8.0 1.00E-03 3.32E-04 6.61E-07 1.65E-03 2.84E-03
12.0 3.88E-04 -1.08E-04 1.10E-06 2.09E-03 3.45E-03
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
SKYHOGG BODY-WING-HORIZONTAL TAIL-VERTICAL TAIL CONFIG

----------------------- 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 0.300 1000.00 333.74 2.0409E+03 515.104 2.0630E+06 225.800 5.750 41.150 7.900 -1.400
0 -------------------DERIVATIVE (PER DEGREE)-------------------
0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB
0
-16.0 0.101 -1.323 0.0846 -1.299 -0.267 -0.065 4.867E-02 2.687E-03 -3.131E-03 6.653E-04 -9.533E-04
-12.0 0.074 -1.066 0.0684 -1.059 -0.149 -0.065 7.868E-02 -3.865E-03 -9.471E-04
-8.0 0.045 -0.693 0.0537 -0.693 -0.052 -0.078 9.398E-02 -4.305E-03 -9.709E-04
-4.0 0.028 -0.315 0.0340 -0.316 0.006 -0.108 9.204E-02 -5.716E-03 -9.951E-04
-2.0 0.025 -0.133 0.0218 -0.134 0.020 -0.163 8.912E-02 -6.690E-03 -1.005E-03
0.0 0.024 0.042 0.0072 0.042 0.024 0.173 8.836E-02 -7.761E-03 -1.012E-03
2.0 0.027 0.220 -0.0093 0.221 0.019 -0.042 9.063E-02 -8.530E-03 -1.020E-03
4.0 0.032 0.404 -0.0269 0.406 0.003 -0.066 9.298E-02 -9.007E-03 -1.029E-03
8.0 0.052 0.784 -0.0645 0.783 -0.058 -0.082 9.116E-02 -1.242E-02 -1.051E-03
12.0 0.082 1.134 -0.1262 1.126 -0.156 -0.112 8.382E-02 -1.845E-02 -1.062E-03
0 ALPHA Q/QINF EPSLON D(EPSLON)/D(ALPHA)
0
-16.0 1.000 -8.088 0.436
-12.0 1.000 -6.342 0.489
-8.0 1.000 -4.172 0.555
-4.0 1.000 -1.901 0.570
-2.0 1.000 -0.758 0.564
0.0 1.000 0.357 0.556
2.0 1.000 1.467 0.556
4.0 0.967 2.580 0.554
8.0 0.869 4.779 0.527
12.0 1.000 6.796 0.504
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
DYNAMIC DERIVATIVES
WING-BODY-VERTICAL TAIL-HORIZONTAL TAIL CONFIGURATION
SKYHOGG BODY-WING-HORIZONTAL TAIL-VERTICAL TAIL CONFIG

----------------------- 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 0.300 1000.00 333.74 2.0409E+03 515.104 2.0630E+06 225.800 5.750 41.150 7.900 -1.400
DYNAMIC DERIVATIVES (PER DEGREE)
0 -------PITCHING------- -----ACCELERATION------ --------------ROLLING-------------- --------YAWING--------
0 ALPHA CLQ CMQ CLAD CMAD CLP CYP CNP CNR CLR
0
-16.00 7.327E-02 -7.613E-02 1.381E-02 -2.933E-02 -4.395E-03 -2.181E-04 1.918E-03 -1.042E-03 -4.394E-03
-12.00 1.548E-02 -3.289E-02 -7.306E-03 -4.026E-04 1.475E-03 -9.784E-04 -3.540E-03
-8.00 1.756E-02 -3.731E-02 -8.776E-03 -7.322E-04 9.068E-04 -8.959E-04 -2.226E-03
-4.00 1.804E-02 -3.832E-02 -8.523E-03 -1.040E-03 4.080E-04 -8.615E-04 -9.047E-04
-2.00 1.786E-02 -3.793E-02 -8.227E-03 -1.182E-03 1.672E-04 -8.631E-04 -2.760E-04
0.00 1.760E-02 -3.738E-02 -8.156E-03 -1.317E-03 -6.955E-05 -8.754E-04 3.273E-04
2.00 1.758E-02 -3.734E-02 -8.395E-03 -1.456E-03 -3.105E-04 -8.980E-04 9.442E-04
4.00 1.695E-02 -3.599E-02 -8.642E-03 -1.601E-03 -5.563E-04 -9.320E-04 1.584E-03
8.00 1.449E-02 -3.078E-02 -8.388E-03 -1.910E-03 -1.085E-03 -1.038E-03 2.906E-03
12.00 1.594E-02 -3.386E-02 -7.488E-03 -2.172E-03 -1.581E-03 -1.174E-03 4.081E-03
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
CHARACTERISTICS OF HIGH LIFT AND CONTROL DEVICES
TAIL PLAIN TRAILING-EDGE FLAP CONFIGURATION
SKYHOGG BODY-WING-HORIZONTAL TAIL-VERTICAL TAIL CONFIG
----------------------- 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 0.300 1000.00 333.74 2.0409E+03 515.104 2.0630E+06 225.800 5.750 41.150 7.900 -1.400
0 ---------INCREMENTS DUE TO DEFLECTION--------- ---DERIVATIVES (PER DEGREE)---
0 DELTA D(CL) D(CM) D(CL MAX) D(CD MIN) (CLA)D (CH)A (CH)D


-20.0 -0.053 0.1015 0.046 0.00425 NDM 2.645E-02 3.969E-02
-10.0 -0.038 0.0726 0.027 0.00157 NDM 3.862E-02
0.0 0.000 -0.0001 0.000 0.00000 NDM 3.862E-02
10.0 0.038 -0.0726 0.027 0.00157 NDM 3.862E-02
20.0 0.053 -0.1016 0.046 0.00425 NDM 3.969E-02
0 *** NOTE * HINGE MOMENT DERIVATIVES ARE BASED ON TWICE THE AREA-MOMENT OF THE CONTROL ABOUT ITS HINGE LINE

0 --------- INDUCED DRAG COEFFICIENT INCREMENT , D(CDI) , DUE TO DEFLECTION ---------
0 DELTA = -20.0 -10.0 0.0 10.0 20.0
ALPHA
0
-16.0 4.84E-03 3.09E-03 -2.07E-06 -1.05E-03 -9.07E-04
-12.0 4.07E-03 2.53E-03 -1.51E-06 -4.93E-04 -1.33E-04
-8.0 3.44E-03 2.08E-03 -1.06E-06 -4.03E-05 4.96E-04
-4.0 2.84E-03 1.65E-03 -6.30E-07 3.87E-04 1.09E-03
-2.0 2.55E-03 1.44E-03 -4.18E-07 5.98E-04 1.38E-03
0.0 2.25E-03 1.22E-03 -2.00E-07 8.17E-04 1.69E-03
2.0 1.94E-03 9.99E-04 2.03E-08 1.04E-03 1.99E-03
4.0 1.63E-03 7.79E-04 2.40E-07 1.26E-03 2.30E-03
8.0 1.02E-03 3.34E-04 6.85E-07 1.70E-03 2.92E-03
12.0 3.35E-04 -1.56E-04 1.17E-06 2.19E-03 3.60E-03
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
SKYHOGG BODY-WING-HORIZONTAL TAIL-VERTICAL TAIL CONFIG

----------------------- 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 0.350 1000.00 389.37 2.0409E+03 515.104 2.4069E+06 225.800 5.750 41.150 7.900 -1.400
0 -------------------DERIVATIVE (PER DEGREE)-------------------
0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB
0
-16.0 0.096 -1.281 0.0882 -1.258 -0.261 -0.070 4.112E-02 1.526E-03 -3.138E-03 6.590E-04 -9.734E-04
-12.0 0.072 -1.051 0.0701 -1.043 -0.148 -0.067 7.324E-02 -4.245E-03 -9.601E-04
-8.0 0.044 -0.695 0.0542 -0.694 -0.053 -0.078 9.171E-02 -4.482E-03 -9.782E-04
-4.0 0.028 -0.317 0.0343 -0.318 0.006 -0.108 9.230E-02 -5.773E-03 -1.001E-03
-2.0 0.024 -0.134 0.0219 -0.135 0.020 -0.162 8.979E-02 -6.742E-03 -1.011E-03
0.0 0.024 0.042 0.0073 0.042 0.024 0.172 8.911E-02 -7.820E-03 -1.018E-03
2.0 0.026 0.222 -0.0094 0.223 0.018 -0.042 9.112E-02 -8.616E-03 -1.026E-03
4.0 0.031 0.407 -0.0272 0.408 0.003 -0.067 9.310E-02 -9.108E-03 -1.035E-03
8.0 0.051 0.785 -0.0652 0.784 -0.059 -0.083 8.819E-02 -1.255E-02 -1.055E-03
12.0 0.079 1.112 -0.1276 1.104 -0.154 -0.116 7.548E-02 -1.865E-02 -1.060E-03
0 ALPHA Q/QINF EPSLON D(EPSLON)/D(ALPHA)
0
-16.0 1.000 -7.957 0.416
-12.0 1.000 -6.291 0.473
-8.0 1.000 -4.176 0.548
-4.0 1.000 -1.907 0.571
-2.0 1.000 -0.761 0.567
0.0 1.000 0.359 0.559
2.0 1.000 1.473 0.557
4.0 0.969 2.587 0.554
8.0 0.870 4.779 0.517
12.0 1.000 6.727 0.487
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
DYNAMIC DERIVATIVES
WING-BODY-VERTICAL TAIL-HORIZONTAL TAIL CONFIGURATION
SKYHOGG BODY-WING-HORIZONTAL TAIL-VERTICAL TAIL CONFIG

----------------------- 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 0.350 1000.00 389.37 2.0409E+03 515.104 2.4069E+06 225.800 5.750 41.150 7.900 -1.400
DYNAMIC DERIVATIVES (PER DEGREE)
0 -------PITCHING------- -----ACCELERATION------ --------------ROLLING-------------- --------YAWING--------
0 ALPHA CLQ CMQ CLAD CMAD CLP CYP CNP CNR CLR
0
-16.00 7.419E-02 -7.711E-02 1.333E-02 -2.832E-02 -3.636E-03 -2.792E-04 1.880E-03 -1.020E-03 -4.301E-03
-12.00 1.513E-02 -3.215E-02 -6.756E-03 -4.318E-04 1.469E-03 -9.727E-04 -3.535E-03
-8.00 1.755E-02 -3.727E-02 -8.537E-03 -7.419E-04 9.125E-04 -8.977E-04 -2.268E-03
-4.00 1.829E-02 -3.885E-02 -8.529E-03 -1.049E-03 4.086E-04 -8.633E-04 -9.282E-04
-2.00 1.814E-02 -3.854E-02 -8.269E-03 -1.192E-03 1.676E-04 -8.647E-04 -2.860E-04
0.00 1.789E-02 -3.799E-02 -8.205E-03 -1.328E-03 -6.974E-05 -8.770E-04 3.330E-04
2.00 1.784E-02 -3.789E-02 -8.413E-03 -1.467E-03 -3.109E-04 -8.998E-04 9.643E-04
4.00 1.718E-02 -3.650E-02 -8.623E-03 -1.611E-03 -5.566E-04 -9.341E-04 1.615E-03
8.00 1.442E-02 -3.063E-02 -8.064E-03 -1.920E-03 -1.092E-03 -1.040E-03 2.954E-03
12.00 1.560E-02 -3.313E-02 -6.626E-03 -2.155E-03 -1.575E-03 -1.165E-03 4.056E-03
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
CHARACTERISTICS OF HIGH LIFT AND CONTROL DEVICES
TAIL PLAIN TRAILING-EDGE FLAP CONFIGURATION
SKYHOGG BODY-WING-HORIZONTAL TAIL-VERTICAL TAIL CONFIG
----------------------- 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 0.350 1000.00 389.37 2.0409E+03 515.104 2.4069E+06 225.800 5.750 41.150 7.900 -1.400
0 ---------INCREMENTS DUE TO DEFLECTION--------- ---DERIVATIVES (PER DEGREE)---
0 DELTA D(CL) D(CM) D(CL MAX) D(CD MIN) (CLA)D (CH)A (CH)D


-20.0 -0.054 0.0996 0.046 0.00426 NDM 2.688E-02 4.068E-02
-10.0 -0.039 0.0712 0.027 0.00158 NDM 3.960E-02
0.0 0.000 -0.0001 0.000 0.00000 NDM 3.960E-02
10.0 0.039 -0.0712 0.027 0.00158 NDM 3.960E-02
20.0 0.054 -0.0997 0.046 0.00426 NDM 4.068E-02
0 *** NOTE * HINGE MOMENT DERIVATIVES ARE BASED ON TWICE THE AREA-MOMENT OF THE CONTROL ABOUT ITS HINGE LINE

0 --------- INDUCED DRAG COEFFICIENT INCREMENT , D(CDI) , DUE TO DEFLECTION ---------
0 DELTA = -20.0 -10.0 0.0 10.0 20.0
ALPHA
0
-16.0 4.92E-03 3.14E-03 -2.12E-06 -1.10E-03 -9.82E-04
-12.0 4.11E-03 2.56E-03 -1.54E-06 -5.21E-04 -1.71E-04
-8.0 3.46E-03 2.09E-03 -1.07E-06 -4.97E-05 4.84E-04
-4.0 2.86E-03 1.66E-03 -6.36E-07 3.83E-04 1.09E-03
-2.0 2.56E-03 1.44E-03 -4.22E-07 5.97E-04 1.38E-03
0.0 2.25E-03 1.22E-03 -2.02E-07 8.16E-04 1.69E-03
2.0 1.95E-03 1.00E-03 1.91E-08 1.04E-03 2.00E-03
4.0 1.64E-03 7.80E-04 2.41E-07 1.26E-03 2.30E-03
8.0 1.01E-03 3.28E-04 6.93E-07 1.71E-03 2.93E-03
12.0 2.96E-04 -1.85E-04 1.21E-06 2.22E-03 3.64E-03
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
SKYHOGG BODY-WING-HORIZONTAL TAIL-VERTICAL TAIL CONFIG

----------------------- 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 0.100 3000.00 110.48 1.8967E+03 507.973 6.5060E+05 225.800 5.750 41.150 7.900 -1.400
0 -------------------DERIVATIVE (PER DEGREE)-------------------
0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB
0
-16.0 0.118 -1.415 0.0769 -1.393 -0.276 -0.055 7.394E-02 5.700E-03 -3.114E-03 7.261E-04 -8.974E-04
-12.0 0.082 -1.085 0.0661 -1.078 -0.145 -0.061 9.077E-02 -2.993E-03 -9.139E-04
-8.0 0.051 -0.689 0.0529 -0.690 -0.045 -0.077 9.686E-02 -4.041E-03 -9.475E-04
-4.0 0.035 -0.310 0.0338 -0.311 0.013 -0.108 9.137E-02 -5.591E-03 -9.752E-04
-2.0 0.031 -0.130 0.0218 -0.131 0.027 -0.166 8.761E-02 -6.572E-03 -9.857E-04
0.0 0.031 0.041 0.0075 0.041 0.031 0.183 8.664E-02 -7.627E-03 -9.936E-04
2.0 0.033 0.216 -0.0087 0.217 0.025 -0.040 8.947E-02 -8.261E-03 -1.002E-03
4.0 0.038 0.399 -0.0256 0.400 0.010 -0.064 9.264E-02 -8.655E-03 -1.013E-03
8.0 0.058 0.780 -0.0621 0.781 -0.051 -0.080 9.765E-02 -1.204E-02 -1.038E-03
12.0 0.093 1.180 -0.1219 1.173 -0.155 -0.104 1.022E-01 -1.788E-02 -1.066E-03
0 ALPHA Q/QINF EPSLON D(EPSLON)/D(ALPHA)
0
-16.0 1.000 -8.375 0.493
-12.0 1.000 -6.403 0.527
-8.0 1.000 -4.161 0.565
-4.0 1.000 -1.885 0.568
-2.0 1.000 -0.750 0.560
0.0 1.000 0.353 0.551
2.0 1.000 1.455 0.552
4.0 0.949 2.563 0.554
8.0 0.856 4.779 0.548
12.0 0.989 6.947 0.542
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
DYNAMIC DERIVATIVES
WING-BODY-VERTICAL TAIL-HORIZONTAL TAIL CONFIGURATION
SKYHOGG BODY-WING-HORIZONTAL TAIL-VERTICAL TAIL CONFIG

----------------------- 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 0.100 3000.00 110.48 1.8967E+03 507.973 6.5060E+05 225.800 5.750 41.150 7.900 -1.400
DYNAMIC DERIVATIVES (PER DEGREE)
0 -------PITCHING------- -----ACCELERATION------ --------------ROLLING-------------- --------YAWING--------
0 ALPHA CLQ CMQ CLAD CMAD CLP CYP CNP CNR CLR
0
-16.00 7.120E-02 -7.387E-02 1.516E-02 -3.220E-02 -6.938E-03 -8.811E-05 1.956E-03 -1.097E-03 -4.582E-03
-12.00 1.621E-02 -3.442E-02 -8.527E-03 -3.591E-04 1.459E-03 -9.893E-04 -3.478E-03
-8.00 1.738E-02 -3.691E-02 -9.090E-03 -7.070E-04 9.013E-04 -8.974E-04 -2.132E-03
-4.00 1.748E-02 -3.713E-02 -8.504E-03 -1.017E-03 4.067E-04 -8.630E-04 -8.532E-04
-2.00 1.722E-02 -3.657E-02 -8.128E-03 -1.159E-03 1.662E-04 -8.648E-04 -2.541E-04
0.00 1.696E-02 -3.601E-02 -8.042E-03 -1.292E-03 -6.911E-05 -8.771E-04 3.147E-04
2.00 1.699E-02 -3.609E-02 -8.345E-03 -1.430E-03 -3.095E-04 -8.993E-04 9.001E-04
4.00 1.619E-02 -3.438E-02 -8.677E-03 -1.575E-03 -5.556E-04 -9.329E-04 1.513E-03
8.00 1.442E-02 -3.063E-02 -9.104E-03 -1.886E-03 -1.066E-03 -1.039E-03 2.802E-03
12.00 1.648E-02 -3.500E-02 -9.403E-03 -2.209E-03 -1.589E-03 -1.200E-03 4.127E-03
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
CHARACTERISTICS OF HIGH LIFT AND CONTROL DEVICES
TAIL PLAIN TRAILING-EDGE FLAP CONFIGURATION
SKYHOGG BODY-WING-HORIZONTAL TAIL-VERTICAL TAIL CONFIG
----------------------- 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 0.100 3000.00 110.48 1.8967E+03 507.973 6.5060E+05 225.800 5.750 41.150 7.900 -1.400
0 ---------INCREMENTS DUE TO DEFLECTION--------- ---DERIVATIVES (PER DEGREE)---
0 DELTA D(CL) D(CM) D(CL MAX) D(CD MIN) (CLA)D (CH)A (CH)D


-20.0 -0.051 0.0894 0.046 0.00422 NDM 2.532E-02 3.655E-02
-10.0 -0.036 0.0639 0.027 0.00156 NDM 3.555E-02
0.0 0.000 -0.0001 0.000 0.00000 NDM 3.555E-02
10.0 0.036 -0.0639 0.027 0.00156 NDM 3.555E-02
20.0 0.051 -0.0895 0.046 0.00422 NDM 3.655E-02
0 *** NOTE * HINGE MOMENT DERIVATIVES ARE BASED ON TWICE THE AREA-MOMENT OF THE CONTROL ABOUT ITS HINGE LINE

0 --------- INDUCED DRAG COEFFICIENT INCREMENT , D(CDI) , DUE TO DEFLECTION ---------
0 DELTA = -20.0 -10.0 0.0 10.0 20.0
ALPHA
0
-16.0 4.38E-03 2.79E-03 -1.86E-06 -9.32E-04 -7.92E-04
-12.0 3.73E-03 2.32E-03 -1.39E-06 -4.65E-04 -1.43E-04
-8.0 3.17E-03 1.92E-03 -9.88E-07 -6.00E-05 4.20E-04
-4.0 2.62E-03 1.52E-03 -5.91E-07 3.37E-04 9.72E-04
-2.0 2.34E-03 1.32E-03 -3.92E-07 5.36E-04 1.25E-03
0.0 2.05E-03 1.11E-03 -1.85E-07 7.43E-04 1.54E-03
2.0 1.77E-03 9.08E-04 2.19E-08 9.49E-04 1.82E-03
4.0 1.48E-03 7.02E-04 2.27E-07 1.15E-03 2.11E-03
8.0 9.09E-04 2.92E-04 6.38E-07 1.57E-03 2.68E-03
12.0 3.22E-04 -1.30E-04 1.06E-06 1.99E-03 3.27E-03
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
SKYHOGG BODY-WING-HORIZONTAL TAIL-VERTICAL TAIL CONFIG

----------------------- 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 0.200 3000.00 220.95 1.8967E+03 507.973 1.3012E+06 225.800 5.750 41.150 7.900 -1.400
0 -------------------DERIVATIVE (PER DEGREE)-------------------
0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB
0
-16.0 0.115 -1.421 0.0775 -1.398 -0.281 -0.055 7.297E-02 5.546E-03 -3.120E-03 6.887E-04 -9.055E-04
-12.0 0.079 -1.092 0.0664 -1.085 -0.150 -0.061 9.081E-02 -3.060E-03 -9.208E-04
-8.0 0.047 -0.695 0.0531 -0.694 -0.050 -0.076 9.748E-02 -4.075E-03 -9.542E-04
-4.0 0.031 -0.312 0.0338 -0.314 0.009 -0.108 9.209E-02 -5.629E-03 -9.818E-04
-2.0 0.027 -0.132 0.0217 -0.132 0.023 -0.164 8.837E-02 -6.615E-03 -9.922E-04
0.0 0.027 0.041 0.0073 0.041 0.027 0.177 8.741E-02 -7.679E-03 -1.000E-03
2.0 0.029 0.218 -0.0090 0.219 0.021 -0.041 9.025E-02 -8.384E-03 -1.009E-03
4.0 0.034 0.402 -0.0262 0.404 0.006 -0.065 9.339E-02 -8.820E-03 -1.019E-03
8.0 0.054 0.786 -0.0632 0.786 -0.056 -0.080 9.800E-02 -1.215E-02 -1.044E-03
12.0 0.089 1.186 -0.1234 1.179 -0.159 -0.105 1.019E-01 -1.797E-02 -1.071E-03
0 ALPHA Q/QINF EPSLON D(EPSLON)/D(ALPHA)
0
-16.0 1.000 -8.392 0.491
-12.0 1.000 -6.426 0.527
-8.0 1.000 -4.178 0.567
-4.0 1.000 -1.893 0.570
-2.0 1.000 -0.753 0.562
0.0 1.000 0.355 0.553
2.0 1.000 1.461 0.555
4.0 0.961 2.574 0.556
8.0 0.864 4.798 0.549
12.0 0.994 6.965 0.542
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
DYNAMIC DERIVATIVES
WING-BODY-VERTICAL TAIL-HORIZONTAL TAIL CONFIGURATION
SKYHOGG BODY-WING-HORIZONTAL TAIL-VERTICAL TAIL CONFIG

----------------------- 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 0.200 3000.00 220.95 1.8967E+03 507.973 1.3012E+06 225.800 5.750 41.150 7.900 -1.400
DYNAMIC DERIVATIVES (PER DEGREE)
0 -------PITCHING------- -----ACCELERATION------ --------------ROLLING-------------- --------YAWING--------
0 ALPHA CLQ CMQ CLAD CMAD CLP CYP CNP CNR CLR
0
-16.00 7.195E-02 -7.453E-02 1.527E-02 -3.244E-02 -6.821E-03 -9.622E-05 1.959E-03 -1.097E-03 -4.660E-03
-12.00 1.637E-02 -3.477E-02 -8.508E-03 -3.638E-04 1.463E-03 -9.892E-04 -3.550E-03
-8.00 1.761E-02 -3.740E-02 -9.125E-03 -7.131E-04 9.026E-04 -8.958E-04 -2.179E-03
-4.00 1.773E-02 -3.766E-02 -8.550E-03 -1.025E-03 4.075E-04 -8.605E-04 -8.743E-04
-2.00 1.747E-02 -3.710E-02 -8.178E-03 -1.168E-03 1.666E-04 -8.621E-04 -2.624E-04
0.00 1.720E-02 -3.653E-02 -8.093E-03 -1.301E-03 -6.925E-05 -8.744E-04 3.193E-04
2.00 1.724E-02 -3.662E-02 -8.393E-03 -1.440E-03 -3.101E-04 -8.968E-04 9.175E-04
4.00 1.661E-02 -3.528E-02 -8.720E-03 -1.586E-03 -5.565E-04 -9.308E-04 1.544E-03
8.00 1.474E-02 -3.130E-02 -9.110E-03 -1.897E-03 -1.068E-03 -1.038E-03 2.857E-03
12.00 1.674E-02 -3.555E-02 -9.347E-03 -2.219E-03 -1.590E-03 -1.200E-03 4.199E-03
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
CHARACTERISTICS OF HIGH LIFT AND CONTROL DEVICES
TAIL PLAIN TRAILING-EDGE FLAP CONFIGURATION
SKYHOGG BODY-WING-HORIZONTAL TAIL-VERTICAL TAIL CONFIG
----------------------- 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 0.200 3000.00 220.95 1.8967E+03 507.973 1.3012E+06 225.800 5.750 41.150 7.900 -1.400
0 ---------INCREMENTS DUE TO DEFLECTION--------- ---DERIVATIVES (PER DEGREE)---
0 DELTA D(CL) D(CM) D(CL MAX) D(CD MIN) (CLA)D (CH)A (CH)D


-20.0 -0.052 0.0842 0.046 0.00424 NDM 2.574E-02 3.805E-02
-10.0 -0.038 0.0601 0.027 0.00157 NDM 3.700E-02
0.0 0.000 -0.0001 0.000 0.00000 NDM 3.700E-02
10.0 0.038 -0.0601 0.027 0.00157 NDM 3.700E-02
20.0 0.052 -0.0843 0.046 0.00424 NDM 3.805E-02
0 *** NOTE * HINGE MOMENT DERIVATIVES ARE BASED ON TWICE THE AREA-MOMENT OF THE CONTROL ABOUT ITS HINGE LINE

0 --------- INDUCED DRAG COEFFICIENT INCREMENT , D(CDI) , DUE TO DEFLECTION ---------
0 DELTA = -20.0 -10.0 0.0 10.0 20.0
ALPHA
0
-16.0 4.59E-03 2.92E-03 -1.93E-06 -9.44E-04 -7.78E-04
-12.0 3.91E-03 2.43E-03 -1.44E-06 -4.57E-04 -1.01E-04
-8.0 3.33E-03 2.01E-03 -1.02E-06 -3.77E-05 4.82E-04
-4.0 2.76E-03 1.60E-03 -6.12E-07 3.73E-04 1.05E-03
-2.0 2.47E-03 1.39E-03 -4.06E-07 5.79E-04 1.34E-03
0.0 2.18E-03 1.18E-03 -1.93E-07 7.93E-04 1.64E-03
2.0 1.88E-03 9.66E-04 2.12E-08 1.01E-03 1.93E-03
4.0 1.58E-03 7.54E-04 2.34E-07 1.22E-03 2.23E-03
8.0 9.91E-04 3.28E-04 6.59E-07 1.64E-03 2.82E-03
12.0 3.81E-04 -1.10E-04 1.10E-06 2.08E-03 3.43E-03
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
SKYHOGG BODY-WING-HORIZONTAL TAIL-VERTICAL TAIL CONFIG

----------------------- 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 0.300 3000.00 331.43 1.8967E+03 507.973 1.9518E+06 225.800 5.750 41.150 7.900 -1.400
0 -------------------DERIVATIVE (PER DEGREE)-------------------
0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB
0
-16.0 0.102 -1.323 0.0847 -1.299 -0.267 -0.065 4.867E-02 2.687E-03 -3.131E-03 6.685E-04 -9.533E-04
-12.0 0.
From: Meagan on 28 Jul 2010 12:51
My message must have been too long. My problem is that I rename the file to datcom.out but when I try to use MATLAB command

data = datcomimport('datcom.out', true, 0)

I get an error message telling me that the file cannot be opened. How do I import my datcom output file into MATLAB?

Thanks for your help,
Meagan
From: Meagan on 28 Jul 2010 12:56
My previous message must have been too long. I renamed my output file to datcom.out. Basically, when I try to use the command:

data = datcomimport('datcom.out', true, 0)

I get an error that the file cannot be opened. What am I doing wrong?

Thanks for your help,
Meagan
From: dpb on 28 Jul 2010 12:54
Meagan wrote:
> Hi all,
>
> I am currently working on a project that requires me to import USAF
> Digital Datcom output files into MATLAB data structures using the
> Aerospace Toolbox. My Datcom output file is:
>
....[Fortran code output file elided]...

And your question is????

doc fgetl
doc sscanf

% will be your friends here as well as perhaps regex...

About all you can do is write code to parse the file structure as it is
on a line-by-line basis to extract whatever pieces you need. textscan()
possibly could be useful for some of the more regular sections as well.

It'll entail counting lines, number of variables/printed line, how to
determine size of problem, etc., etc., etc., ...

--
From: dpb on 28 Jul 2010 13:22
Meagan wrote:
> My previous message must have been too long. I renamed my output file to
> datcom.out. Basically, when I try to use the command:
> data = datcomimport('datcom.out', true, 0)
>
> I get an error that the file cannot be opened. What am I doing wrong?

what do you get from

dir 'datcom.out'

? I'd presume the file isn't in the working directory or a directory in
the Matlab path. If so, specify where it is, add the path or otherwise
resolve the problem in locating the file.

Ignore my other response; I don't have the appropriate toolbox and
therefore didn't realize there was a function already prepared to parse
an output file of the type...

--
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