[HEADER]
VERSION=2

[WING_0]					; Wing identifier. A car can have as many wings as necessary.
NAME=BODY					; name of the wing
CHORD=1.12					; length of the wing in meters
SPAN=1.4					; width of the wing in meters. both help determine the frontal area of the wing. Single unit is used to simplify calculations
POSITION=0,0.31,1				; 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=1.12					; length of the wing in meters
SPAN=1.4					; width of the wing in meters. both help determine the frontal area of the wing. Single unit is used to simplify calculations
POSITION=0,0.1,1.7				; 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=1.12					; length of the wing in meters
SPAN=1.4					; width of the wing in meters. both help determine the frontal area of the wing. Single unit is used to simplify calculations
POSITION=0,0.45,-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)