0        1:Type(-)      Type[0=Plane] ParDesigner Ver0.8
60       2:Tmax(N)      Maximum Thrust
0.05     3:Drmax(rad)   Maximun Rudder Angle
0.029    4:Demax(rad)   Maxmim Elevator Angle
0.001    5:Damax(rad)   Maximim Aileron Angle
1.0      6:CLmax(-)     Maximum Lift Coefficient
-1.0     7:CLmin(-)     Minimum Lift Coefficient
8        8:CLa(/rad)    Lift Gradient
0        9:CLaSt(/rad)  Lift Gradient in Stall
0.018    10:CDw(-)      Drag Coefficient of Wing
0.02     11:CDb(-)      Drag Coefficient of Fuselage
0.4      12:mug(-)      Friction Coefficient of Wheels
0.76     13:dCDSt(-)    Rise of Drag Coefficient in Stall
0.00     14:CM(-)       Moment Coefficient
0.0074   15:alpha0(rad) Wing Angle
2.42     16:b(m)        Wing Span
0.32     17:c(m)        Wing Chord
0.08     18:hce(m)      Equivalent Center of Gravity
2.5      19:m(Kg)       Mass
0.11     20:Izz(Kg*m^2) Yaw Inertia Moment
0.085    21:Iyy(Kg*m^2) Pitch Inertia Moment
0.06     22:Ixx(Kg*m^2) Roll Inertia Moment
0.09     23:She(m^2)    Effective Area of Stab
0.03     24:Sfe(m^2)    Effective Area of fin
1        25:Lt(m)       Tail Moment Arm
0.002    26:VForm(-)    Effect of Dihedral Angle