// aerofly professional --------------------------------------------------------
//
// file:    AS_LCF.tmd
// version: 1.6.0
//
// type:    17
// lock:    0
//
// -----------------------------------------------------------------------------


Append tmdjoint00 JointFuselageEngine
Append tmdjoint00 JointFuselageAntenna
Append tmdjoint00 JointFuselageLeftwingstruts
Append tmdjoint00 JointFuselageRightwingstruts
Append tmdjoint00 JointLeftgearLeftskid
Append tmdjoint00 JointRightgearRightskid
Append tmdjoint00 JointLeftgearFrontstruts
Append tmdjoint00 JointRightgearBackstruts
Append tmdjoint00 JointFuselageLeftwing
Append tmdjoint00 JointFuselageRightwing
Append tmdjoint00 JointFuselageStabilizer
Append tmdjoint00 JointFuselageLeftstabilizer
Append tmdjoint00 JointFuselageRightstabilizer
Append tmdjoint00 JointFuselageLeftgear
Append tmdjoint00 JointFuselageRightgear
Append tmdfuselage00 Fuselage
Append tmdgear00 Leftgear
Append tmdgear00 Rightgear
Append tmdskid00 Leftskid
Append tmdskid00 Rightskid
Append tmdbody Antenna
Append tmdbody Frontstruts
Append tmdbody Backstruts
Append tmdbody Leftwingstruts
Append tmdbody Rightwingstruts
Append tmdwing00 Leftwing
Append tmdwing00 Rightwing
Append tmdwing10 Leftstabilizer
Append tmdwing10 Rightstabilizer
Append tmdwing11 Stabilizer
Append tmdservo00 ServoLeftaileron
Append tmdservo00 ServoRightaileron
Append tmdservo00 ServoLeftflap
Append tmdservo00 ServoRightflap
Append tmdservo00 ServoRudder
Append tmdservo00 ServoElevator
Append tmdpropeller00 Propeller
Append tmdengine10 Engine
Append tmdservo00 ServoThrottle
Append tmdreceiver00 Receiver
cd JointFuselageEngine/
X    = tmvector4r(   1.0000,   0.0000,   0.0000, 0 )
Y    = tmvector4r(   0.0000,   1.0000,   0.0000, 0 )
Z    = tmvector4r(   0.0000,   0.0000,   1.0000, 0 )
R    = tmvector4r(   0.0000,   0.0000,   0.0000, 1 )
Mass = 0
RangeMassMax = 0
RangeMassMin = 0
Inertia = {   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000 }
Kn = 1000
Dn = 20
Dv = 5
Body0 = ../Fuselage/
Body1 = ../Engine/
Kf = 10000
Df = 100
Ktx = 1000
Dtx = 10
Kty = 1000
Dty = 10
Ktz = 1000
Dtz = 10
MaxForce = 0
MaxTorque = 0
Rigid = 1
Essential = 1
Angle = 0
AngleZ = 0
Axis = tmvector4r(   0.0000,   0.0000,   0.0000, 0 )
Displacement = tmvector4r(   0.0000,   0.0000,   0.0000, 0 )
cd ../

cd JointFuselageAntenna/
X    = tmvector4r(   1.0000,   0.0000,   0.0000, 0 )
Y    = tmvector4r(   0.0000,   1.0000,   0.0000, 0 )
Z    = tmvector4r(   0.0000,   0.0000,   1.0000, 0 )
R    = tmvector4r(   0.0000,   0.0000,   0.0000, 1 )
Mass = 0
RangeMassMax = 0
RangeMassMin = 0
Inertia = {   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000 }
Kn = 1000
Dn = 20
Dv = 5
Body0 = ../Fuselage/
Body1 = ../Antenna/
Kf = 10000
Df = 100
Ktx = 1000
Dtx = 10
Kty = 1000
Dty = 10
Ktz = 1000
Dtz = 10
MaxForce = 0
MaxTorque = 0
Rigid = 1
Essential = 1
Angle = 0
AngleZ = 0
Axis = tmvector4r(   0.0000,   0.0000,   0.0000, 0 )
Displacement = tmvector4r(   0.0000,   0.0000,   0.0000, 0 )
cd ../

cd JointFuselageLeftwingstruts/
X    = tmvector4r(   1.0000,   0.0000,   0.0000, 0 )
Y    = tmvector4r(   0.0000,   1.0000,   0.0000, 0 )
Z    = tmvector4r(   0.0000,   0.0000,   1.0000, 0 )
R    = tmvector4r(   0.0000,   0.0000,   0.0000, 1 )
Mass = 0
RangeMassMax = 0
RangeMassMin = 0
Inertia = {   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000 }
Kn = 1000
Dn = 20
Dv = 5
Body0 = ../Fuselage/
Body1 = ../Leftwingstruts/
Kf = 10000
Df = 100
Ktx = 1000
Dtx = 10
Kty = 1000
Dty = 10
Ktz = 1000
Dtz = 10
MaxForce = 0
MaxTorque = 0
Rigid = 1
Essential = 1
Angle = 0
AngleZ = 0
Axis = tmvector4r(   0.0000,   0.0000,   0.0000, 0 )
Displacement = tmvector4r(   0.0000,   0.0000,   0.0000, 0 )
cd ../

cd JointFuselageRightwingstruts/
X    = tmvector4r(   1.0000,   0.0000,   0.0000, 0 )
Y    = tmvector4r(   0.0000,   1.0000,   0.0000, 0 )
Z    = tmvector4r(   0.0000,   0.0000,   1.0000, 0 )
R    = tmvector4r(   0.0000,   0.0000,   0.0000, 1 )
Mass = 0
RangeMassMax = 0
RangeMassMin = 0
Inertia = {   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000 }
Kn = 1000
Dn = 20
Dv = 5
Body0 = ../Fuselage/
Body1 = ../Rightwingstruts/
Kf = 10000
Df = 100
Ktx = 1000
Dtx = 10
Kty = 1000
Dty = 10
Ktz = 1000
Dtz = 10
MaxForce = 0
MaxTorque = 0
Rigid = 1
Essential = 1
Angle = 0
AngleZ = 0
Axis = tmvector4r(   0.0000,   0.0000,   0.0000, 0 )
Displacement = tmvector4r(   0.0000,   0.0000,   0.0000, 0 )
cd ../

cd JointLeftgearLeftskid/
X    = tmvector4r(   1.0000,   0.0000,   0.0000, 0 )
Y    = tmvector4r(   0.0000,   1.0000,   0.0000, 0 )
Z    = tmvector4r(   0.0000,   0.0000,   1.0000, 0 )
R    = tmvector4r(   0.0000,   0.0000,   0.0000, 1 )
Mass = 0
RangeMassMax = 0
RangeMassMin = 0
Inertia = {   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000 }
Kn = 1000
Dn = 20
Dv = 5
Body0 = ../Leftgear/
Body1 = ../Leftskid/
Kf = 10000
Df = 100
Ktx = 1000
Dtx = 10
Kty = 1000
Dty = 10
Ktz = 1000
Dtz = 10
MaxForce = 0
MaxTorque = 0
Rigid = 1
Essential = 1
Angle = 0
AngleZ = 0
Axis = tmvector4r(   0.0000,   0.0000,   0.0000, 0 )
Displacement = tmvector4r(   0.0000,   0.0000,   0.0000, 0 )
cd ../

cd JointRightgearRightskid/
X    = tmvector4r(   1.0000,   0.0000,   0.0000, 0 )
Y    = tmvector4r(   0.0000,   1.0000,   0.0000, 0 )
Z    = tmvector4r(   0.0000,   0.0000,   1.0000, 0 )
R    = tmvector4r(   0.0000,   0.0000,   0.0000, 1 )
Mass = 0
RangeMassMax = 0
RangeMassMin = 0
Inertia = {   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000 }
Kn = 1000
Dn = 20
Dv = 5
Body0 = ../Rightgear/
Body1 = ../Rightskid/
Kf = 10000
Df = 100
Ktx = 1000
Dtx = 10
Kty = 1000
Dty = 10
Ktz = 1000
Dtz = 10
MaxForce = 0
MaxTorque = 0
Rigid = 1
Essential = 1
Angle = 0
AngleZ = 0
Axis = tmvector4r(   0.0000,   0.0000,   0.0000, 0 )
Displacement = tmvector4r(   0.0000,   0.0000,   0.0000, 0 )
cd ../

cd JointLeftgearFrontstruts/
X    = tmvector4r(   1.0000,   0.0000,   0.0000, 0 )
Y    = tmvector4r(   0.0000,   1.0000,   0.0000, 0 )
Z    = tmvector4r(   0.0000,   0.0000,   1.0000, 0 )
R    = tmvector4r(   0.0000,   0.0000,   0.0000, 1 )
Mass = 0
RangeMassMax = 0
RangeMassMin = 0
Inertia = {   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000 }
Kn = 1000
Dn = 20
Dv = 5
Body0 = ../Leftgear/
Body1 = ../Frontstruts/
Kf = 10000
Df = 100
Ktx = 1000
Dtx = 10
Kty = 1000
Dty = 10
Ktz = 1000
Dtz = 10
MaxForce = 0
MaxTorque = 0
Rigid = 1
Essential = 1
Angle = 0
AngleZ = 0
Axis = tmvector4r(   0.0000,   0.0000,   0.0000, 0 )
Displacement = tmvector4r(   0.0000,   0.0000,   0.0000, 0 )
cd ../

cd JointRightgearBackstruts/
X    = tmvector4r(   1.0000,   0.0000,   0.0000, 0 )
Y    = tmvector4r(   0.0000,   1.0000,   0.0000, 0 )
Z    = tmvector4r(   0.0000,   0.0000,   1.0000, 0 )
R    = tmvector4r(   0.0000,   0.0000,   0.0000, 1 )
Mass = 0
RangeMassMax = 0
RangeMassMin = 0
Inertia = {   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000 }
Kn = 1000
Dn = 20
Dv = 5
Body0 = ../Rightgear/
Body1 = ../Backstruts/
Kf = 10000
Df = 100
Ktx = 1000
Dtx = 10
Kty = 1000
Dty = 10
Ktz = 1000
Dtz = 10
MaxForce = 0
MaxTorque = 0
Rigid = 1
Essential = 1
Angle = 0
AngleZ = 0
Axis = tmvector4r(   0.0000,   0.0000,   0.0000, 0 )
Displacement = tmvector4r(   0.0000,   0.0000,   0.0000, 0 )
cd ../

cd JointFuselageLeftwing/
X    = tmvector4r(   1.0000,   0.0000,   0.0000, 0 )
Y    = tmvector4r(   0.0000,   1.0000,   0.0000, 0 )
Z    = tmvector4r(   0.0000,   0.0000,   1.0000, 0 )
R    = tmvector4r(   0.0906,   0.0000,   0.2354, 1 )
Mass = 0
RangeMassMax = 0
RangeMassMin = 0
Inertia = {   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000 }
Kn = 1000
Dn = 20
Dv = 5
Body0 = ../Fuselage/
Body1 = ../Leftwing/
Kf = 30000
Df = 30
Ktx = 4000
Dtx = 4
Kty = 4000
Dty = 4
Ktz = 4000
Dtz = 4
MaxForce = 8000
MaxTorque = 800
Rigid = 1
Essential = 1
Angle = 0
AngleZ = 0
Axis = tmvector4r(   0.0000,   0.0000,   0.0000, 0 )
Displacement = tmvector4r(   0.0000,   0.0000,   0.0000, 0 )
cd ../

cd JointFuselageRightwing/
X    = tmvector4r(   1.0000,   0.0000,   0.0000, 0 )
Y    = tmvector4r(   0.0000,   1.0000,   0.0000, 0 )
Z    = tmvector4r(   0.0000,   0.0000,   1.0000, 0 )
R    = tmvector4r(   0.0906,   0.0000,   0.2354, 1 )
Mass = 0
RangeMassMax = 0
RangeMassMin = 0
Inertia = {   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000 }
Kn = 1000
Dn = 20
Dv = 5
Body0 = ../Fuselage/
Body1 = ../Rightwing/
Kf = 30000
Df = 30
Ktx = 4000
Dtx = 4
Kty = 4000
Dty = 4
Ktz = 4000
Dtz = 4
MaxForce = 8000
MaxTorque = 800
Rigid = 1
Essential = 1
Angle = 0
AngleZ = 0
Axis = tmvector4r(   0.0000,   0.0000,   0.0000, 0 )
Displacement = tmvector4r(   0.0000,   0.0000,   0.0000, 0 )
cd ../

cd JointFuselageStabilizer/
X    = tmvector4r(   1.0000,   0.0000,   0.0000, 0 )
Y    = tmvector4r(   0.0000,   1.0000,   0.0000, 0 )
Z    = tmvector4r(   0.0000,   0.0000,   1.0000, 0 )
R    = tmvector4r(  -1.3914,   0.0000,  -0.0028, 1 )
Mass = 0
RangeMassMax = 0
RangeMassMin = 0
Inertia = {   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000 }
Kn = 1000
Dn = 20
Dv = 5
Body0 = ../Fuselage/
Body1 = ../Stabilizer/
Kf = 10000
Df = 5
Ktx = 1000
Dtx = 4
Kty = 1000
Dty = 4
Ktz = 1000
Dtz = 4
MaxForce = 1000
MaxTorque = 1000
Rigid = 0
Essential = 1
Angle = 0
AngleZ = 0
Axis = tmvector4r(   0.0000,   0.0000,   0.0000, 0 )
Displacement = tmvector4r(   0.0000,   0.0000,   0.0000, 0 )
cd ../

cd JointFuselageLeftstabilizer/
X    = tmvector4r(   1.0000,   0.0000,   0.0000, 0 )
Y    = tmvector4r(   0.0000,   1.0000,   0.0000, 0 )
Z    = tmvector4r(   0.0000,   0.0000,   1.0000, 0 )
R    = tmvector4r(  -1.3884,   0.0041,   0.1234, 1 )
Mass = 0
RangeMassMax = 0
RangeMassMin = 0
Inertia = {   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000 }
Kn = 1000
Dn = 20
Dv = 5
Body0 = ../Fuselage/
Body1 = ../Leftstabilizer/
Kf = 5000
Df = 5
Ktx = 500
Dtx = 1.4
Kty = 500
Dty = 1.4
Ktz = 500
Dtz = 1.4
MaxForce = 1800
MaxTorque = 500
Rigid = 0
Essential = 1
Angle = 0
AngleZ = 0
Axis = tmvector4r(   0.0000,   0.0000,   0.0000, 0 )
Displacement = tmvector4r(   0.0000,   0.0000,   0.0000, 0 )
cd ../

cd JointFuselageRightstabilizer/
X    = tmvector4r(   1.0000,   0.0000,   0.0000, 0 )
Y    = tmvector4r(   0.0000,   1.0000,   0.0000, 0 )
Z    = tmvector4r(   0.0000,   0.0000,   1.0000, 0 )
R    = tmvector4r(  -1.3884,  -0.0041,   0.1234, 1 )
Mass = 0
RangeMassMax = 0
RangeMassMin = 0
Inertia = {   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000 }
Kn = 1000
Dn = 20
Dv = 5
Body0 = ../Fuselage/
Body1 = ../Rightstabilizer/
Kf = 5000
Df = 5
Ktx = 500
Dtx = 1.4
Kty = 500
Dty = 1.4
Ktz = 500
Dtz = 1.4
MaxForce = 1800
MaxTorque = 500
Rigid = 0
Essential = 1
Angle = 0
AngleZ = 0
Axis = tmvector4r(   0.0000,   0.0000,   0.0000, 0 )
Displacement = tmvector4r(   0.0000,   0.0000,   0.0000, 0 )
cd ../

cd JointFuselageLeftgear/
X    = tmvector4r(   1.0000,   0.0000,   0.0000, 0 )
Y    = tmvector4r(   0.0000,   1.0000,   0.0000, 0 )
Z    = tmvector4r(   0.0000,   0.0000,   1.0000, 0 )
R    = tmvector4r(   0.2436,   0.0620,  -0.1490, 1 )
Mass = 0
RangeMassMax = 0
RangeMassMin = 0
Inertia = {   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000 }
Kn = 1000
Dn = 20
Dv = 5
Body0 = ../Fuselage/
Body1 = ../Leftgear/
Kf = 10000
Df = 20
Ktx = 780
Dtx = 3
Kty = 1800
Dty = 2
Ktz = 1800
Dtz = 2
MaxForce = 4000
MaxTorque = 500
Rigid = 0
Essential = 1
Angle = 0
AngleZ = 0
Axis = tmvector4r(   0.0000,   0.0000,   0.0000, 0 )
Displacement = tmvector4r(   0.0000,   0.0000,   0.0000, 0 )
cd ../

cd JointFuselageRightgear/
X    = tmvector4r(   1.0000,   0.0000,   0.0000, 0 )
Y    = tmvector4r(   0.0000,   1.0000,   0.0000, 0 )
Z    = tmvector4r(   0.0000,   0.0000,   1.0000, 0 )
R    = tmvector4r(   0.2436,  -0.0620,  -0.1490, 1 )
Mass = 0
RangeMassMax = 0
RangeMassMin = 0
Inertia = {   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000 }
Kn = 1000
Dn = 20
Dv = 5
Body0 = ../Fuselage/
Body1 = ../Rightgear/
Kf = 10000
Df = 20
Ktx = 780
Dtx = 3
Kty = 1800
Dty = 2
Ktz = 1800
Dtz = 2
MaxForce = 4000
MaxTorque = 500
Rigid = 0
Essential = 1
Angle = 0
AngleZ = 0
Axis = tmvector4r(   0.0000,   0.0000,   0.0000, 0 )
Displacement = tmvector4r(   0.0000,   0.0000,   0.0000, 0 )
cd ../

cd Fuselage/
X    = tmvector4r(   1.0000,   0.0000,   0.0000, 0 )
Y    = tmvector4r(   0.0000,   1.0000,   0.0000, 0 )
Z    = tmvector4r(   0.0000,   0.0000,   1.0000, 0 )
R    = tmvector4r(   0.1301,  -0.0001,  -0.0550, 1 )
Geometry( "~Geometry/Fuselage/" )
Mass = 12
RangeMassMax = 19.9978
RangeMassMin = 4.99944
Inertia = {   0.4203,   0.0001,  -0.0584,   0.0000,   0.0001,   2.2008,  -0.0000,   0.0000,  -0.0584,  -0.0000,   2.1869,   0.0000,   0.0000,   0.0000,   0.0000, 3360.3647 }
Kn = 1000
Dn = 20
Dv = 0.2
AreaCenter = tmvector4r(   0.0000,   0.0000,   0.0490, 1 )
CG = tmvector4r(  -0.0300,   0.0000,   0.0000, 1 )
SmokeR = tmvector4r(   0.0000,   0.0000,   0.0000, 1 )
Cdx = 0.7
Cly = 0.7
Cdy = 2
Clz = 1
Cdz = 2
InertiaScale = 0
cd ../

cd Leftgear/
MountingR = tmvector4f(   0.2436,   0.0620,  -0.1490,   1.0000 )
MountingZ = tmvector4f(   1.0000,   0.0000,   0.0000,   0.0000 )
Retractable = 0
RetractZ = tmvector4f(   1.0000,   0.0000,   0.0000,   0.0000 )
RetractAngle = 0
RetractAngleZ = 0
Cdx = 0
X    = tmvector4r(   1.0000,   0.0000,   0.0000, 0 )
Y    = tmvector4r(   0.0000,   0.8107,  -0.5855, 0 )
Z    = tmvector4r(   0.0000,   0.5855,   0.8107, 0 )
R    = tmvector4r(  -0.1492,   0.2536,  -0.2832, 1 )
Geometry( "~Geometry/Leftgear/" )
Mass = 0.25
RangeMassMax = 0
RangeMassMin = 0
Inertia = {   0.0015,  -0.0002,   0.0000,   0.0000,  -0.0002,   0.0001,   0.0000,   0.0000,   0.0000,   0.0000,   0.0016,   0.0000,   0.0000,   0.0000,   0.0000, 134.0529 }
Kn = 0
Dn = 0
Dv = 0
cd ../

cd Rightgear/
MountingR = tmvector4f(   0.2436,  -0.0620,  -0.1490,   1.0000 )
MountingZ = tmvector4f(   1.0000,   0.0000,   0.0000,   0.0000 )
Retractable = 0
RetractZ = tmvector4f(   1.0000,   0.0000,   0.0000,   0.0000 )
RetractAngle = 0
RetractAngleZ = 0
Cdx = 0
X    = tmvector4r(   1.0000,   0.0000,   0.0000, 0 )
Y    = tmvector4r(   0.0000,   0.8107,   0.5855, 0 )
Z    = tmvector4r(   0.0000,  -0.5855,   0.8107, 0 )
R    = tmvector4r(  -0.1492,  -0.2536,  -0.2832, 1 )
Geometry( "~Geometry/Rightgear/" )
Mass = 0.25
RangeMassMax = 0
RangeMassMin = 0
Inertia = {   0.0015,   0.0002,   0.0000,   0.0000,   0.0002,   0.0001,  -0.0000,   0.0000,   0.0000,  -0.0000,   0.0016,   0.0000,   0.0000,   0.0000,   0.0000, 134.0529 }
Kn = 0
Dn = 0
Dv = 0
cd ../

cd Leftskid/
X    = tmvector4r(   0.9997,   0.0001,  -0.0236, 0 )
Y    = tmvector4r(  -0.0001,   1.0000,   0.0000, 0 )
Z    = tmvector4r(   0.0000,   0.0000,   0.9997, 0 )
R    = tmvector4r(  -0.0608,   0.3620,  -0.3296, 1 )
Geometry( "~Geometry/Leftskid/" )
Mass = 0.1
RangeMassMax = 0
RangeMassMin = 0
Inertia = {   0.0036,   0.0000,   0.0000,   0.0000,   0.0000,   0.0739,   0.0000,   0.0000,   0.0000,   0.0000,   0.0740,   0.0000,   0.0000,   0.0000,   0.0000,  64.2977 }
Kn = 500
Dn = 20
Dv = 0.2
CP1 = tmvector4r(   0.6871,   0.3619,  -0.4472, 1 )
CP2 = tmvector4r(  -0.6762,   0.3619,  -0.3618, 1 )
Ksn = 5000
Dsn = 30
Ksx = 0.5
cd ../

cd Rightskid/
X    = tmvector4r(   0.9997,  -0.0001,  -0.0236, 0 )
Y    = tmvector4r(   0.0001,   1.0000,   0.0000, 0 )
Z    = tmvector4r(   0.0000,   0.0000,   0.9997, 0 )
R    = tmvector4r(  -0.0608,  -0.3620,  -0.3296, 1 )
Geometry( "~Geometry/Rightskid/" )
Mass = 0.1
RangeMassMax = 0
RangeMassMin = 0
Inertia = {   0.0036,   0.0000,   0.0000,   0.0000,   0.0000,   0.0739,   0.0000,   0.0000,   0.0000,   0.0000,   0.0740,   0.0000,   0.0000,   0.0000,   0.0000,  64.2977 }
Kn = 500
Dn = 20
Dv = 0.2
CP1 = tmvector4r(   0.6871,  -0.3619,  -0.4472, 1 )
CP2 = tmvector4r(  -0.6762,  -0.3619,  -0.3618, 1 )
Ksn = 5000
Dsn = 30
Ksx = 0.5
cd ../

cd Antenna/
X    = tmvector4r(   0.9998,   0.0017,  -0.0201, 0 )
Y    = tmvector4r(  -0.0014,   0.9999,   0.0141, 0 )
Z    = tmvector4r(   0.0201,  -0.0141,   0.9997, 0 )
R    = tmvector4r(  -0.0724,   0.4328,   0.0105, 1 )
Geometry( "~Geometry/Antenna/" )
Mass = 0.5
RangeMassMax = 1
RangeMassMin = 0.25
Inertia = {   0.0029,  -0.0000,   0.0000,   0.0000,  -0.0000,   0.0268,  -0.0000,   0.0000,   0.0000,  -0.0000,   0.0274,   0.0000,   0.0000,   0.0000,   0.0000, 1024.4258 }
Kn = 0
Dn = 0
Dv = 0
cd ../

cd Leftwingstruts/
X    = tmvector4r(   0.9998,   0.0017,  -0.0201, 0 )
Y    = tmvector4r(  -0.0014,   0.9999,   0.0141, 0 )
Z    = tmvector4r(   0.0201,  -0.0141,   0.9997, 0 )
R    = tmvector4r(  -0.0724,   0.4328,   0.0105, 1 )
Geometry( "~Geometry/Leftwingstruts/" )
Mass = 0.5
RangeMassMax = 1
RangeMassMin = 0.25
Inertia = {   0.0029,  -0.0000,   0.0000,   0.0000,  -0.0000,   0.0268,  -0.0000,   0.0000,   0.0000,  -0.0000,   0.0274,   0.0000,   0.0000,   0.0000,   0.0000, 1024.4258 }
Kn = 0
Dn = 0
Dv = 0
cd ../

cd Rightwingstruts/
X    = tmvector4r(   0.9998,   0.0017,  -0.0201, 0 )
Y    = tmvector4r(  -0.0014,   0.9999,   0.0141, 0 )
Z    = tmvector4r(   0.0201,  -0.0141,   0.9997, 0 )
R    = tmvector4r(  -0.0724,   0.4328,   0.0105, 1 )
Geometry( "~Geometry/Rightwingstruts/" )
Mass = 0.5
RangeMassMax = 1
RangeMassMin = 0.25
Inertia = {   0.0029,  -0.0000,   0.0000,   0.0000,  -0.0000,   0.0268,  -0.0000,   0.0000,   0.0000,  -0.0000,   0.0274,   0.0000,   0.0000,   0.0000,   0.0000, 1024.4258 }
Kn = 0
Dn = 0
Dv = 0
cd ../

cd Frontstruts/
X    = tmvector4r(   0.9998,   0.0017,  -0.0201, 0 )
Y    = tmvector4r(  -0.0014,   0.9999,   0.0141, 0 )
Z    = tmvector4r(   0.0201,  -0.0141,   0.9997, 0 )
R    = tmvector4r(  -0.0724,   0.4328,   0.0105, 1 )
Geometry( "~Geometry/Frontstruts/" )
Mass = 0.5
RangeMassMax = 1
RangeMassMin = 0.25
Inertia = {   0.0029,  -0.0000,   0.0000,   0.0000,  -0.0000,   0.0268,  -0.0000,   0.0000,   0.0000,  -0.0000,   0.0274,   0.0000,   0.0000,   0.0000,   0.0000, 1024.4258 }
Kn = 0
Dn = 0
Dv = 0
cd ../

cd Backstruts/
X    = tmvector4r(   0.9998,   0.0017,  -0.0201, 0 )
Y    = tmvector4r(  -0.0014,   0.9999,   0.0141, 0 )
Z    = tmvector4r(   0.0201,  -0.0141,   0.9997, 0 )
R    = tmvector4r(  -0.0724,   0.4328,   0.0105, 1 )
Geometry( "~Geometry/Backstruts/" )
Mass = 0.5
RangeMassMax = 1
RangeMassMin = 0.25
Inertia = {   0.0029,  -0.0000,   0.0000,   0.0000,  -0.0000,   0.0268,  -0.0000,   0.0000,   0.0000,  -0.0000,   0.0274,   0.0000,   0.0000,   0.0000,   0.0000, 1024.4258 }
Kn = 0
Dn = 0
Dv = 0
cd ../

cd Leftwing/
Sections = 2
RootR = tmvector4f(   0.0906,   0.0000,   0.2354,   1.0000 )
RootN = tmvector4f(   0.0000,   1.0000,   0.0000,   0.0000 )
PropWashFactor = 0.3
FuselageInterference = 1
Cly = 0.7
RangeSpanMax = 2.77961
RangeSpanMin = 0.694903
IncidenceOffset = 0
FlapEffect = 0
Aileron = ~Geometry/Leftwing/Leftaileron/
AileronLink = ~Aircraft/ServoLeftaileron/MechLink
Flap = ~Geometry/Leftwing/Leftflap/
FlapDisplacement = tmvector4f(   0.0000,   0.0000,   0.0000,   0.0000 )
FlapLink = ~Aircraft/ServoLeftflap/MechLink
Flap1Displacement = tmvector4f(   0.0000,   0.0000,   0.0000,   0.0000 )
AirbrakeDisplacement = 0
AirbrakeCl = 1
AirbrakeCd = 1
// start section 0
SectionR(0)     = tmvector4f(   0.1338,  -0.3841,   0.0110,   1.0000 )
SectionArea(0)  =   0.5993
SectionChord(0) =   0.5841
SectionAirfoil(0) = "NACA 2415"
// start section 1
SectionR(1)     = tmvector4f(   0.1204,   0.5854,  -0.0011,   1.0000 )
SectionArea(1)  =   0.4519
SectionChord(1) =   0.4701
SectionAirfoil(1) = "NACA 0015"
X    = tmvector4r(   1.0000,  -0.0055,   0.0082, 0 )
Y    = tmvector4r(   0.0050,   0.9981,   0.0611, 0 )
Z    = tmvector4r(  -0.0085,  -0.0610,   0.9981, 0 )
R    = tmvector4r(  -0.0809,   0.8724,   0.2213, 1 )
Geometry( "~Geometry/Leftwing/" )
Mass = 2
RangeMassMax = 2.4
RangeMassMin = 0.6
Inertia = {   0.5885,  -0.0000,  -0.0000,   0.0000,  -0.0000,   0.0585,  -0.0000,   0.0000,  -0.0000,  -0.0000,   0.6358,   0.0000,   0.0000,   0.0000,   0.0000, 215.7396 }
Kn = 1000
Dn = 10
Dv = 0.2
cd ../

cd Rightwing/
Sections = 2
RootR = tmvector4f(   0.0906,   0.0000,   0.2354,   1.0000 )
RootN = tmvector4f(   0.0000,  -1.0000,   0.0000,   0.0000 )
PropWashFactor = 0.3
FuselageInterference = 1
Cly = 0.7
RangeSpanMax = 2.77964
RangeSpanMin = 0.69491
IncidenceOffset = 0
FlapEffect = 0
Aileron = ~Geometry/Rightwing/Rightaileron/
AileronLink = ~Aircraft/ServoRightaileron/MechLink
Flap = ~Geometry/Rightwing/Rightflap/
FlapDisplacement = tmvector4f(   0.0000,   0.0000,   0.0000,   0.0000 )
FlapLink = ~Aircraft/ServoRightflap/MechLink
Flap1Displacement = tmvector4f(   0.0000,   0.0000,   0.0000,   0.0000 )
AirbrakeDisplacement = 0
AirbrakeCl = 1
AirbrakeCd = 1
// start section 0
SectionR(0)     = tmvector4f(   0.1337,   0.3838,   0.0112,   1.0000 )
SectionArea(0)  =   0.5993
SectionChord(0) =   0.5851
SectionAirfoil(0) = "NACA 2415"
// start section 1
SectionR(1)     = tmvector4f(   0.1203,  -0.5857,  -0.0011,   1.0000 )
SectionArea(1)  =   0.4520
SectionChord(1) =   0.4699
SectionAirfoil(1) = "NACA 0015"
X    = tmvector4r(   1.0000,   0.0056,   0.0080, 0 )
Y    = tmvector4r(  -0.0051,   0.9981,  -0.0611, 0 )
Z    = tmvector4r(  -0.0084,   0.0610,   0.9981, 0 )
R    = tmvector4r(  -0.0810,  -0.8721,   0.2213, 1 )
Geometry( "~Geometry/Rightwing/" )
Mass = 2
RangeMassMax = 2.4
RangeMassMin = 0.6
Inertia = {   0.5888,   0.0000,  -0.0000,   0.0000,   0.0000,   0.0585,   0.0000,   0.0000,  -0.0000,   0.0000,   0.6361,   0.0000,   0.0000,   0.0000,   0.0000, 215.7713 }
Kn = 1000
Dn = 10
Dv = 0.2
cd ../

cd Leftstabilizer/
Sections = 1
RootR = tmvector4f(  -1.3884,   0.0041,   0.1234,   1.0000 )
RootN = tmvector4f(   0.0000,   0.0000,   0.0000,   0.0000 )
Flap = ~Geometry/Leftstabilizer/Leftelevator/
FlapLink = ~Aircraft/ServoElevator/MechLink
FlapRotation = 0.8
PropWashFactor = 0.75
RangeSpanMax = 1.01946
RangeSpanMin = 0.254865
// start section 0
SectionR(0)     = tmvector4f(   0.0819,   0.0531,   0.0001,   1.0000 )
SectionArea(0)  =   0.1760
SectionChord(0) =   0.3491
SectionAirfoil(0) = "NACA 0015"
X    = tmvector4r(   1.0000,  -0.0000,  -0.0019, 0 )
Y    = tmvector4r(   0.0000,   1.0000,  -0.0001, 0 )
Z    = tmvector4r(   0.0019,   0.0001,   1.0000, 0 )
R    = tmvector4r(  -1.5584,   0.2922,  -0.0425, 1 )
Geometry( "~Geometry/Leftstabilizer/" )
Mass = 0.4
RangeMassMax = 0.4
RangeMassMin = 0.1
Inertia = {   0.0107,   0.0006,   0.0000,   0.0000,   0.0006,   0.0043,   0.0000,   0.0000,   0.0000,   0.0000,   0.0149,   0.0000,   0.0000,   0.0000,   0.0000, 150.1633 }
Kn = 10000
Dn = 40
Dv = 0.2
cd ../

cd Rightstabilizer/
Sections = 1
RootR = tmvector4f(  -1.3884,  -0.0041,   0.1234,   1.0000 )
RootN = tmvector4f(   0.0000,   0.0000,   0.0000,   0.0000 )
Flap = ~Geometry/Rightstabilizer/Rightelevator/
FlapLink = ~Aircraft/ServoElevator/MechLink
FlapRotation = 0.8
PropWashFactor = 0.75
RangeSpanMax = 1.01946
RangeSpanMin = 0.254865
// start section 0
SectionR(0)     = tmvector4f(   0.0819,  -0.0531,   0.0001,   1.0000 )
SectionArea(0)  =   0.1760
SectionChord(0) =   0.3491
SectionAirfoil(0) = "NACA 0015"
X    = tmvector4r(   1.0000,   0.0000,  -0.0019, 0 )
Y    = tmvector4r(   0.0000,   1.0000,   0.0001, 0 )
Z    = tmvector4r(   0.0019,  -0.0001,   1.0000, 0 )
R    = tmvector4r(  -1.5584,  -0.2922,  -0.0425, 1 )
Geometry( "~Geometry/Rightstabilizer/" )
Mass = 0.4
RangeMassMax = 0.4
RangeMassMin = 0.1
Inertia = {   0.0107,  -0.0006,   0.0000,   0.0000,  -0.0006,   0.0043,  -0.0000,   0.0000,   0.0000,  -0.0000,   0.0149,   0.0000,   0.0000,   0.0000,   0.0000, 150.1632 }
Kn = 10000
Dn = 40
Dv = 0.2
cd ../

cd Stabilizer/
Sections = 1
RootR = tmvector4f(  -1.3914,   0.0000,  -0.0028,   1.0000 )
RootN = tmvector4f(   0.0000,   0.0000,   0.0000,   0.0000 )
Flap = ~Geometry/Stabilizer/Rudder/
FlapLink = ~Aircraft/ServoRudder/MechLink
FlapRotation = 0.8
PropWashFactor = 1
RangeSpanMax = 0.624322
RangeSpanMin = 0.15608
// start section 0
SectionR(0)     = tmvector4f(  -0.0652,  -0.0656,  -0.0002,   1.0000 )
SectionArea(0)  =   0.3192
SectionChord(0) =   0.4244
SectionAirfoil(0) = "NACA 0015"
X    = tmvector4r(   1.0000,   0.0001,  -0.0000, 0 )
Y    = tmvector4r(   0.0000,  -0.0006,  -1.0000, 0 )
Z    = tmvector4r(  -0.0001,   1.0000,  -0.0006, 0 )
R    = tmvector4r(  -1.5020,   0.0011,   0.1237, 1 )
Geometry( "~Geometry/Stabilizer/" )
Mass = 0.6
RangeMassMax = 0.8
RangeMassMin = 0.2
Inertia = {   0.0139,  -0.0147,  -0.0000,   0.0000,  -0.0147,   0.0544,   0.0000,   0.0000,  -0.0000,   0.0000,   0.0681,   0.0000,   0.0000,   0.0000,   0.0000, 197.1563 }
Kn = 10000
Dn = 40
Dv = 0.2
cd ../

cd ServoLeftaileron/
SignalIn = ~Aircraft/Receiver/Out(10)
P0 = 0
P1 = 0.523599
P2 = 0
P3 = 0
PFirst = 0
Vmax = 10
X    = tmvector4r(   1.0000,   0.0000,   0.0000, 0 )
Y    = tmvector4r(   0.0000,   1.0000,   0.0000, 0 )
Z    = tmvector4r(   0.0000,   0.0000,   1.0000, 0 )
R    = tmvector4r(   0.0000,   0.0000,   0.0000, 1 )
Mass = 0
RangeMassMax = 0
RangeMassMin = 0
Inertia = {   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000 }
Kn = 1000
Dn = 20
Dv = 5
cd ../

cd ServoRightaileron/
SignalIn = ~Aircraft/Receiver/Out(11)
P0 = 0
P1 = -0.523599
P2 = 0
P3 = 0
PFirst = 0
Vmax = 10
X    = tmvector4r(   1.0000,   0.0000,   0.0000, 0 )
Y    = tmvector4r(   0.0000,   1.0000,   0.0000, 0 )
Z    = tmvector4r(   0.0000,   0.0000,   1.0000, 0 )
R    = tmvector4r(   0.0000,   0.0000,   0.0000, 1 )
Mass = 0
RangeMassMax = 0
RangeMassMin = 0
Inertia = {   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000 }
Kn = 1000
Dn = 20
Dv = 5
cd ../

cd ServoLeftflap/
SignalIn = ~Aircraft/Receiver/Out(12)
P0 = 0.349066
P1 = 0.349066
P2 = 0
P3 = 0
PFirst = 0
Vmax = 1
X    = tmvector4r(   1.0000,   0.0000,   0.0000, 0 )
Y    = tmvector4r(   0.0000,   1.0000,   0.0000, 0 )
Z    = tmvector4r(   0.0000,   0.0000,   1.0000, 0 )
R    = tmvector4r(   0.0000,   0.0000,   0.0000, 1 )
Mass = 0
RangeMassMax = 0
RangeMassMin = 0
Inertia = {   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000 }
Kn = 1000
Dn = 20
Dv = 5
cd ../

cd ServoRightflap/
SignalIn = ~Aircraft/Receiver/Out(13)
P0 = 0.349066
P1 = 0.349066
P2 = 0
P3 = 0
PFirst = 0
Vmax = 1
X    = tmvector4r(   1.0000,   0.0000,   0.0000, 0 )
Y    = tmvector4r(   0.0000,   1.0000,   0.0000, 0 )
Z    = tmvector4r(   0.0000,   0.0000,   1.0000, 0 )
R    = tmvector4r(   0.0000,   0.0000,   0.0000, 1 )
Mass = 0
RangeMassMax = 0
RangeMassMin = 0
Inertia = {   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000 }
Kn = 1000
Dn = 20
Dv = 5
cd ../

cd ServoRudder/
SignalIn = ~Aircraft/Receiver/Out(8)
P0 = 0
P1 = 0.698132
P2 = 0
P3 = 0
PFirst = 0
Vmax = 10
X    = tmvector4r(   1.0000,   0.0000,   0.0000, 0 )
Y    = tmvector4r(   0.0000,   1.0000,   0.0000, 0 )
Z    = tmvector4r(   0.0000,   0.0000,   1.0000, 0 )
R    = tmvector4r(   0.0000,   0.0000,   0.0000, 1 )
Mass = 0
RangeMassMax = 0
RangeMassMin = 0
Inertia = {   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000 }
Kn = 1000
Dn = 20
Dv = 5
cd ../

cd ServoElevator/
SignalIn = ~Aircraft/Receiver/Out(4)
P0 = 0
P1 = 0.610865
P2 = 0
P3 = 0
PFirst = 0
Vmax = 10
X    = tmvector4r(   1.0000,   0.0000,   0.0000, 0 )
Y    = tmvector4r(   0.0000,   1.0000,   0.0000, 0 )
Z    = tmvector4r(   0.0000,   0.0000,   1.0000, 0 )
R    = tmvector4r(   0.0000,   0.0000,   0.0000, 1 )
Mass = 0
RangeMassMax = 0
RangeMassMin = 0
Inertia = {   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000 }
Kn = 1000
Dn = 20
Dv = 5
cd ../

cd Propeller/
X    = tmvector4r(   0.0000,   1.0000,   0.0000, 0 )
Y    = tmvector4r(   0.0000,   0.0000,   1.0000, 0 )
Z    = tmvector4r(   1.0000,   0.0000,   0.0000, 0 )
R    = tmvector4r(   0.7761,  -0.0000,   0.0075, 1 )
Geometry( "~Geometry/Propeller/" )
Mass = 0.4
RangeMassMax = 0.5
RangeMassMin = 0.1
Inertia = {   0.0004,   0.0000,   0.0000,   0.0000,   0.0000,   0.0004,   0.0000,   0.0000,   0.0000,   0.0000,   0.0004,   0.0000,   0.0000,   0.0000,   0.0000,   1.0000 }
Kn = 4000
Dn = 10
Dv = 5
Radius = 0.2794
RangeRadiusMax = 0.558801
RangeRadiusMin = 0.1397
Pitch  = 0.254005
DragLateral  = 0.001
Engine = ~Aircraft/Engine/
cd ../

cd Engine/
X    = tmvector4r(   1.0000,   0.0000,   0.0000, 0 )
Y    = tmvector4r(   0.0000,   1.0000,   0.0000, 0 )
Z    = tmvector4r(   0.0000,   0.0000,   1.0000, 0 )
R    = tmvector4r(   0.0073,   0.0000,   0.0000, 1 )
Mass = 1.918
RangeMassMax = 0
RangeMassMin = 0
Inertia = {   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0007,   0.0000,   0.0000,   0.0000,   0.0000,   0.0007,   0.0000,   0.0000,   0.0000,   0.0000,   2.1168 }
Kn = 4000
Dn = 10
Dv = 5
ThrottleControl = ~Aircraft/ServoThrottle/MechLink
Sound0File = "CE172E"
Sound0RPM = 10000.000000
Sound0RPMLow = 0.000000
TorqueFactor = 0.100000
ConstantRPM = 0
MotorNs = 300.000000
MotorRi = 0.003500
MotorI0 = 2.000000
MotorMass = 0.350000
MotorR = tmvector4r(   0.0400,   0.0000,   0.0000, 1 )
CellNum = 28
CellVoltage = 1.200000
CellMass = 0.056000
CellRi = 0.002000
CellR = tmvector4r(   0.0000,   0.0000,   0.0000, 1 )
GearRatio = 2.000000
GearMass = 0.000000
GearEta = 1.000000
cd ../

cd ServoThrottle/
SignalIn = ~Aircraft/Receiver/Out(0)
P0 = 0
P1 = 1
P2 = 0
P3 = 0
PFirst = -1
Vmax = 2
X    = tmvector4r(   1.0000,   0.0000,   0.0000, 0 )
Y    = tmvector4r(   0.0000,   1.0000,   0.0000, 0 )
Z    = tmvector4r(   0.0000,   0.0000,   1.0000, 0 )
R    = tmvector4r(   0.0000,   0.0000,   0.0000, 1 )
Mass = 0
RangeMassMax = 0
RangeMassMin = 0
Inertia = {   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000 }
Kn = 1000
Dn = 20
Dv = 5
cd ../

cd Receiver/
X    = tmvector4r(   1.0000,   0.0000,   0.0000, 0 )
Y    = tmvector4r(   0.0000,   1.0000,   0.0000, 0 )
Z    = tmvector4r(   0.0000,   0.0000,   1.0000, 0 )
R    = tmvector4r(   0.0000,   0.0000,   0.0000, 1 )
Mass = 0
RangeMassMax = 0
RangeMassMin = 0
Inertia = {   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000,   0.0000 }
Kn = 1000
Dn = 20
Dv = 5
VTailMixElevator = 0.77
VTailMixRudder   = 0.42
cd ../