[HEADER]

VERSION=2



[WING_0]

NAME=BODY							; name of the wing

CHORD=1								; length of the wing in meters

SPAN=2.0								; width of the wing in meters. both help determine the frontal area

POSITION=0,0.24,-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							; Coefficient of drag multiplier (for easy fine tuning)

ANGLE=3
ZONE_FRONT_CL=0     ; CL=CL/(1.0+ZONE_0_CL*DAMAGE)

ZONE_FRONT_CD=0.005    ; CD=CD*(1.0+ZONE_0_CD*DAMAGE)

ZONE_REAR_CL=0     ; CL=CL/(1.0+ZONE_0_CL*DAMAGE)

ZONE_REAR_CD=0.005     ; CD=CD*(1.0+ZONE_0_CD*DAMAGE)

ZONE_LEFT_CL=0     ; CL=CL/(1.0+ZONE_0_CL*DAMAGE)

ZONE_LEFT_CD=0.01     ; CD=CD*(1.0+ZONE_0_CD*DAMAGE)

ZONE_RIGHT_CL=0     ; CL=CL/(1.0+ZONE_0_CL*DAMAGE)

ZONE_RIGHT_CD=0.01     ; CD=CD*(1.0+ZONE_0_CD*DAMAGE)



[WING_1]

NAME=FRONT							; name of the wing

CHORD=1								; length of the wing in meters

SPAN=2.0								; width of the wing in meters. both help determine the frontal area

POSITION=0,-0.28,1.700						; position in x,y,z starting from the CoG

LUT_AOA_CL=wing_front_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_front_AOA_CD.lut		; Coefficient of drag lookup table

LUT_GH_CD=							; Height aero drag multiplier table

CD_GAIN=0							; Coefficient of drag multiplier (for easy fine tuning)

ANGLE=0

ZONE_FRONT_CL=0.015    ; CL=CL/(1.0+ZONE_0_CL*DAMAGE)

ZONE_FRONT_CD=0.015    ; CD=CD*(1.0+ZONE_0_CD*DAMAGE)

ZONE_REAR_CL=0     ; CL=CL/(1.0+ZONE_0_CL*DAMAGE)

ZONE_REAR_CD=0     ; CD=CD*(1.0+ZONE_0_CD*DAMAGE)

ZONE_LEFT_CL=0     ; CL=CL/(1.0+ZONE_0_CL*DAMAGE)

ZONE_LEFT_CD=0     ; CD=CD*(1.0+ZONE_0_CD*DAMAGE)

ZONE_RIGHT_CL=0     ; CL=CL/(1.0+ZONE_0_CL*DAMAGE)

ZONE_RIGHT_CD=0     ; CD=CD*(1.0+ZONE_0_CD*DAMAGE)



[WING_2]

NAME=REAR							; name of the wing

CHORD=1								; length of the wing in meters

SPAN=2.0								; width of the wing in meters. both help determine the frontal area

POSITION=0,0.95,-1.70						; 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=0							; Coefficient of drag multiplier (for easy fine tuning)

ANGLE=0
ZONE_FRONT_CL=0    ; CL=CL/(1.0+ZONE_0_CL*DAMAGE)

ZONE_FRONT_CD=0    ; CD=CD*(1.0+ZONE_0_CD*DAMAGE)

ZONE_REAR_CL=0.01     ; CL=CL/(1.0+ZONE_0_CL*DAMAGE)

ZONE_REAR_CD=0.015     ; CD=CD*(1.0+ZONE_0_CD*DAMAGE)

ZONE_LEFT_CL=0     ; CL=CL/(1.0+ZONE_0_CL*DAMAGE)

ZONE_LEFT_CD=0     ; CD=CD*(1.0+ZONE_0_CD*DAMAGE)

ZONE_RIGHT_CL=0     ; CL=CL/(1.0+ZONE_0_CL*DAMAGE)

ZONE_RIGHT_CD=0     ; CD=CD*(1.0+ZONE_0_CD*DAMAGE)