0        1:Type(-)      Type[0=Plane] ParDesigner Ver0.8
150      2:Tmax(N)      Maximum Thrust
0.10     3:Drmax(rad)   Maximun Rudder Angle
0.125    4:Demax(rad)   Maxmim Elevator Angle
0.012    5:Damax(rad)   Maximim Aileron Angle
1.0      6:CLmax(-)     Maximum Lift Coefficient
-1.0     7:CLmin(-)     Minimum Lift Coefficient
0.8      8:CLa(/rad)    Lift Gradient
30       9:CLaSt(/rad)  Lift Gradient in Stall
0.002    10:CDw(-)      Drag Coefficient of Wing
0.002    11:CDb(-)      Drag Coefficient of Fuselage
0.53     12:mug(-)      Friction Coefficient of Wheels
0.2      13:dCDSt(-)    Rise of Drag Coefficient in Stall
0.01     14:CM(-)       Moment Coefficient
-0.0001  15:alpha0(rad) Wing Angle
2.5      16:b(m)        Wing Span
0.32     17:c(m)        Wing Chord
0.8      18:hce(m)      Equivalent Center of Gravity
4        19:m(Kg)       Mass
0.5      20:Izz(Kg*m^2) Yaw Inertia Moment
0.4      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        24:Sfe(m^2)    Effective Area of fin
2        25:Lt(m)       Tail Moment Arm
0.18     26:VForm(-)    Effect of Dihedral Angle