0 1:Type(-) Type[0=Plane] ParDesigner Ver0.8
4 2:Tmax(N) Maximum Thrust
1.8 3rmax(rad) Maximun Rudder Angle
1.4 4emax(rad) Maxmim Elevator Angle
0.4 5amax(rad) Maximim Aileron Angle
1.0 6:CLmax(-) Maximum Lift Coefficient
-1.0 7:CLmin(-) Minimum Lift Coefficient
1 8:CLa(/rad) Lift Gradient
20 9:CLaSt(/rad) Lift Gradient in Stall
0.02 10:CDw(-) Drag Coefficient of Wing
0.01 11:CDb(-) Drag Coefficient of Fuselage
0.1 12:mug(-) Friction Coefficient of Wheels
0.1 13:dCDSt(-) Rise of Drag Coefficient in Stall
0.03 14:CM(-) Moment Coefficient
0.00 15:alpha0(rad) Wing Angle
1.5 16:b(m) Wing Span
0.6 17:c(m) Wing Chord
0.45 18:hce(m) Equivalent Center of Gravity
0.2 19:m(Kg) Mass
1.2 20:Izz(Kg*m^2) Yaw Inertia Moment
1.2 21:Iyy(Kg*m^2) Pitch Inertia Moment
0.1 22:Ixx(Kg*m^2) Roll Inertia Moment
1.5 23:She(m^2) Effective Area of Stab
1.5 24:Sfe(m^2) Effective Area of fin
1.5 25:Lt(m) Tail Moment Arm
0.000 26:VForm(-) Effect of Dihedral Angle


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