[HEADER]
VERSION=3

[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=1.79								; width of the wing in meters. both help determine the frontal area of the wing. Single unit is used to simplify calculations
POSITION=0,-0.15,-0.3						; 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=1.0								; 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=0.013    ; CD=CD*(1.0+ZONE_0_CD*DAMAGE)
ZONE_REAR_CL=0     ; CL=CL/(1.0+ZONE_0_CL*DAMAGE)
ZONE_REAR_CD=0.013     ; CD=CD*(1.0+ZONE_0_CD*DAMAGE)
ZONE_LEFT_CL=0     ; CL=CL/(1.0+ZONE_0_CL*DAMAGE)
ZONE_LEFT_CD=0.013     ; CD=CD*(1.0+ZONE_0_CD*DAMAGE)
ZONE_RIGHT_CL=0     ; CL=CL/(1.0+ZONE_0_CL*DAMAGE)
ZONE_RIGHT_CD=0.013     ; CD=CD*(1.0+ZONE_0_CD*DAMAGE)
YAW_CL_GAIN=0.0

[WING_1]
NAME=FRONT
CHORD=1.0
SPAN=1.79
POSITION=0,-0.33,1.7
LUT_AOA_CL=wing_front_AOA_CL.lut
LUT_GH_CL=height_frontwing_CL.lut						
CL_GAIN=1.0
LUT_AOA_CD=wing_front_AOA_CD.lut
LUT_GH_CD=height_frontwing_CD.lut						
CD_GAIN=1.0
ANGLE=0
ZONE_FRONT_CL=0.09    ; CL=CL/(1.0+ZONE_0_CL*DAMAGE)
ZONE_FRONT_CD=0.08    ; 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)
YAW_CL_GAIN=-0.02

[WING_2]
NAME=REAR
CHORD=1.0
SPAN=1.79
POSITION=0,0.1,-1.995
LUT_AOA_CL=wing_rear_AOA_CL.lut
LUT_GH_CL=							
CL_GAIN=1.0
LUT_AOA_CD=wing_rear_AOA_CD.lut
LUT_GH_CD=						
CD_GAIN=1.0
ANGLE=1
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=0.05     ; CL=CL/(1.0+ZONE_0_CL*DAMAGE)
ZONE_REAR_CD=0.08     ; 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)
YAW_CL_GAIN=-0.03