[HEADER]

VERSION=2



[WING_0]					; Wing identifier. A car can have as many wings as necessary.

NAME=BODY					; name of the wing

CHORD=1.0					; length of the wing in meters

SPAN=1.62					; width of the wing in meters. both help determine the frontal area of the wing. Single unit is used to simplify calculations

POSITION=0,0.04,0.2				; 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 (for easy fine tuning) 

LUT_AOA_CD=wing_body_AOA_CD.lut			; Coefficient of drag lookup table

LUT_GH_CD=					; Height aero drag multiplier table

CD_GAIN=1.4					; Coefficient of drag multiplier (for easy fine tuning)

ANGLE=0					        ; Default starting wing angle (degrees)

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

ZONE_FRONT_CD=0.002    				; CD=CD*(1.0+ZONE_0_CD*DAMAGE)

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

ZONE_REAR_CD=0.002     				; CD=CD*(1.0+ZONE_0_CD*DAMAGE)

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

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

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

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



[WING_1]					; Wing identifier. A car can have as many wings as necessary.

NAME=FRONT					; name of the wing

CHORD=1.0					; length of the wing in meters

SPAN=1.62					; width of the wing in meters. both help determine the frontal area of the wing. Single unit is used to simplify calculations

POSITION=0,-0.10,1.6				; 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 (for easy fine tuning) 

LUT_AOA_CD=wing_front_AOA_CL.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					        ; Default starting wing angle (degrees)

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

ZONE_FRONT_CD=0.002    				; CD=CD*(1.0+ZONE_0_CD*DAMAGE)

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

ZONE_REAR_CD=0.002    				; CD=CD*(1.0+ZONE_0_CD*DAMAGE)

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

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

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

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



[WING_2]					; Wing identifier. A car can have as many wings as necessary.

NAME=REAR					; name of the wing

CHORD=1.0					; length of the wing in meters

SPAN=1.62					; width of the wing in meters. both help determine the frontal area of the wing. Single unit is used to simplify calculations

POSITION=0,0.35,-1.7				; 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 (for easy fine tuning) 

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					        ; Default starting wing angle (degrees)

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

ZONE_FRONT_CD=0.002    				; CD=CD*(1.0+ZONE_0_CD*DAMAGE)

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

ZONE_REAR_CD=0.002     				; CD=CD*(1.0+ZONE_0_CD*DAMAGE)

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

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

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

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