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Info-Mac 3
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Science
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Cessna Simulation 0.3.2
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EFS
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Cessna172.dat
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1993-11-28
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EFS_0.3
mass_lb 2645.
Ixx_US 948.
Ixy_US 0.
Iyy_US 1346.
Ixz_US 0.
Iyz_US 0.
Izz_US 1967.
Sref_sqft 174.
bref_ft 35.8.
cref_ft 4.9
AltPowerEng
Pmax_hp 160.
ADisk_sqft 28.
thrustlag_sec 1.
/*********
Set the DL flag to 0 if data is given for X-Z coordinates,
1 for D-L coordinates. Set the AutoReflect flag to nonzero if
the drag curve should be reflected for negative angle of
attack.
*********/
DL 1
AutoReflect 0
GearN
x_ft 4.5
y_ft 0.0
zmin_ft 3.2
zmax_ft 5.0
omega2 44.13
zeta 1.00
mu 0.40
GearL
x_ft -0.9
y_ft -3.6
zmin_ft 3.2
zmax_ft 5.0
omega2 44.13
zeta 1.00
mu 0.40
GearR
x_ft -0.9
y_ft 3.6
zmin_ft 3.2
zmax_ft 5.0
omega2 44.13
zeta 1.00
mu 0.40
dAmax_deg 10.0
dEmax_deg 10.0
dPmax_deg 10.0
StickMapA
-1.00 -1.00
1.00 1.00
StickMapE
-1.00 -1.00
1.00 1.00
TrimE 0.0
/*********
Control mixing matrix.
Rows are aileron, elevator, and rudder gains.
Columns are commanded aileron, elevator, and rudder deflections.
*********/
FeedForward_deg
10.0000 0.00000 0.00000
0.00000 10.0000 0.00000
0.00000 0.00000 10.0000
/*********
Angular feedback matrix.
Rows are aileron, elevator, and rudder gains.
Columns are phi, theta, and psi states.
*********/
AngularFeedBack
0.000 0.000 -.1745
0.000 0.000 0.000
0.000 0.000 0.000
/*********
Proportional feedback matrix.
Rows are aileron, elevator, and rudder gains.
Columns are a, b, p, q, r.
*********/
StateFeedBack
0.00 0.00 0.00 0.00 0.00
0.00 0.00 0.00 0.00 0.00
0.00 0.00 0.00 0.00 0.00
AccelFeedback_rad_SI
0 0 0 0 0 0
0 0 0 0 0 0
0 0 0 0 0 0
/* Just guesses here. */
CDdF .060
CLdF .43
CMdF -.11
CDdB .0
/*********
Aero coefficients
First number is the angle of attack for which the coefficients hold.
Rows are Cx, Cy, Cz, Cl, Cm, Cn.
Columns are 0, a, b, ad, p, q, r, dA, dE, dP.
*********/
CData
Alpha_deg -3.9
0.03100 0.13000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 -0.06000 0.00000
0.00000 0.00000 -0.31000 0.00000 -0.03700 0.00000 0.21000 0.00000 0.00000 -0.18700
-0.31000 4.60000 0.00000 1.70000 0.00000 3.90000 0.00000 0.00000 -0.43000 0.00000
0.00000 0.00000 -0.08900 0.00000 -0.47000 0.00000 0.09600 0.17800 0.00000 -0.01470
0.12120 -0.89000 0.00000 -5.20000 0.00000 -12.4000 0.00000 0.00000 1.28000 0.00000
0.00000 0.00000 0.06500 0.00000 -0.03000 0.00000 -0.09900 -0.05300 0.00000 0.06570
CData
Alpha_deg 0.0
0.02200 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 -0.06000 0.00000
0.00000 0.00000 -0.31000 0.00000 -0.03700 0.00000 0.21000 0.00000 0.00000 -0.18700
0.00000 4.60000 0.00000 1.70000 0.00000 3.90000 0.00000 0.00000 -0.43000 0.00000
0.00000 0.00000 -0.08900 0.00000 -0.47000 0.00000 0.09600 0.17800 0.00000 -0.01470
0.06060 -0.89000 0.00000 -5.20000 0.00000 -12.4000 0.00000 0.00000 1.28000 0.00000
0.00000 0.00000 0.06500 0.00000 -0.03000 0.00000 -0.09900 -0.05300 0.00000 0.06570
CData
Alpha_deg 3.9
0.03100 0.13000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 -0.06000 0.00000
0.00000 0.00000 -0.31000 0.00000 -0.03700 0.00000 0.21000 0.00000 0.00000 -0.18700
0.31000 4.60000 0.00000 1.70000 0.00000 3.90000 0.00000 0.00000 -0.43000 0.00000
0.00000 0.00000 -0.08900 0.00000 -0.47000 0.00000 0.09600 0.17800 0.00000 -0.01470
0.00000 -0.89000 0.00000 -5.20000 0.00000 -12.4000 0.00000 0.00000 1.28000 0.00000
0.00000 0.00000 0.06500 0.00000 -0.03000 0.00000 -0.09900 -0.05300 0.00000 0.06570
end