0        1:Type(-)      Type[0=Plane] ParDesigner Ver0.8
5        2:Tmax(N)      Maximum Thrust
0.0      3:Drmax(rad)   Maximun Rudder Angle
0.15     4:Demax(rad)   Maxmim Elevator Angle
0.01     5:Damax(rad)   Maximim Aileron Angle
1.0      6:CLmax(-)     Maximum Lift Coefficient
-0.3     7:CLmin(-)     Minimum Lift Coefficient
6.2      8:CLa(/rad)    Lift Gradient
2        9:CLaSt(/rad)  Lift Gradient in Stall
0.05     10:CDw(-)      Drag Coefficient of Wing
0.07     11:CDb(-)      Drag Coefficient of Fuselage
0.05     12:mug(-)      Friction Coefficient of Wheels
0.05     13:dCDSt(-)    Rise of Drag Coefficient in Stall
0        14:CM(-)       Moment Coefficient
0.07     15:alpha0(rad) Wing Angle
0.890    16:b(m)        Wing Span
0.2      17:c(m)        Wing Chord
0.08     18:hce(m)      Equivalent Center of Gravity
0.555    19:m(Kg)       Mass
0.015    20:Izz(Kg*m^2) Yaw Inertia Moment
0.01     21:Iyy(Kg*m^2) Pitch Inertia Moment
0.001    22:Ixx(Kg*m^2) Roll Inertia Moment
0.06     23:She(m^2)    Effective Area of Stab
0.05     24:Sfe(m^2)    Effective Area of fin
0.7      25:Lt(m)       Tail Moment Arm
0.05     26:VForm(-)    Effect of Dihedral Angle
