[HEADER]
VERSION=1



[WING_0]
NAME=BODY							; name of the wing
CHORD=1								; length of the wing in meters
SPAN=1.8							; width of the wing in meters. both help determine the frontal area
POSITION=0,0.23,-0.40						; position in x,y,z starting from the CoG
LUT_AOA_CL=wing_body_AOA_CL.lut		; Coefficient of Lift lookup table
LUT_GH_CL=							; Height aero lift multiplier lookup table
CL_GAIN=0							; Coefficient of Lift multiplier 
LUT_AOA_CD=wing_body_AOA_CD.lut		; Coefficient of drag lookup table
LUT_GH_CD=							; Height aero drag multiplier table
CD_GAIN=1.3							; Coefficient of drag multiplier (for easy fine tuning)
ANGLE=0


[WING_1]
NAME=REAR							; name of the wing
CHORD=0.18							; length of the wing in meters
SPAN=1.5								; width of the wing in meters. both help determine the frontal area
POSITION=0.0,0.55,-2.2						; position in x,y,z starting from the CoG
LUT_AOA_CL=wing_rear_AOA_CL.lut		; Coefficient of Lift lookup table
LUT_GH_CL=							; Height aero lift multiplier lookup table
CL_GAIN=1							; Coefficient of Lift multiplier 
LUT_AOA_CD=wing_rear_AOA_CD.lut		; Coefficient of drag lookup table
LUT_GH_CD=							; Height aero drag multiplier table
CD_GAIN=1							; Coefficient of drag multiplier (for easy fine tuning)
ANGLE=5