[HEADER]
VERSION=2

[WING_0]
NAME=BODY							; name of the wing
CHORD=1								; length of the wing in meters
SPAN=1.94 ;1.90 no fspoiler, 1.96 fspoiler
POSITION=0,0.300,-0.31273					; position in x,y,z starting from the CoG
LUT_AOA_CL=empty.lut		; Coefficient of Lift lookup table
LUT_GH_CL=empty.lut							; 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=wing_body_GH_CD.lut							; Height aero drag multiplier table
CD_GAIN=0.98							; 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=0.005    ; 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=0.50								; length of the wing in meters
SPAN=1.65								; width of the wing in meters. both help determine the frontal area
POSITION=0,-0.290,1.63727						; 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=wing_front_GH_CL.lut							; Height aero lift multiplier lookup table
CL_GAIN=1							; Coefficient of Lift multiplier 
LUT_AOA_CD=empty.lut		; Coefficient of drag lookup table
LUT_GH_CD=empty.lut							; 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=0.8								; length of the wing in meters
SPAN=1.65								; width of the wing in meters. both help determine the frontal area
POSITION=0,-0.310,-1.86273						; 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=wing_rear_GH_CL.lut						; Height aero lift multiplier lookup table
CL_GAIN=0.70							; Coefficient of Lift multiplier 
LUT_AOA_CD=empty.lut		; Coefficient of drag lookup table
LUT_GH_CD=empty.lut							; 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)

[WING_3]
NAME=REAR AEROFOIL							; name of the wing
CHORD=0.31								; length of the wing in meters
SPAN=1.41								; width of the wing in meters. both help determine the frontal area
POSITION=0,0.560,-2.1206						; position in x,y,z starting from the CoG
LUT_AOA_CL=wing_rfoil_AOA_CL.lut		; Coefficient of Lift lookup table
LUT_GH_CL=empty.lut							; Height aero lift multiplier lookup table
CL_GAIN=0.50						; Coefficient of Lift multiplier 
LUT_AOA_CD=wing_rfoil_AOA_CD.lut		; Coefficient of drag lookup table
LUT_GH_CD=empty.lut							; Height aero drag multiplier table
CD_GAIN=0.70							; Coefficient of drag multiplier (for easy fine tuning)
ANGLE=5
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     ; 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=-0.250

[WING_4]								; Wing identifier. A car can have as many wings as necessary.
NAME=UNDERTRAY								; name of the wing
CHORD=1.10								; length of the wing in meters
SPAN=0.85								; width of the wing in meters. both help determine the frontal area of the wing. Single unit is used to simplify calculations
POSITION=0,-0.330,0.9694						; position in x,y,z starting from the CoG
LUT_AOA_CL=wing_ftray_AOA_CL.lut			; Coefficient of Lift lookup table
LUT_GH_CL=wing_ftray_GH_CL.lut				; Height aero lift multiplier lookup table
CL_GAIN=1									; Coefficient of Lift multiplier (for easy fine tuning) 
LUT_AOA_CD=empty.lut			; Coefficient of drag lookup table
LUT_GH_CD=empty.lut							; Height aero drag multiplier table
CD_GAIN=0								; Coefficient of drag multiplier (for easy fine tuning)
ANGLE=0
YAW_CL_GAIN=-0.250
ZONE_FRONT_CL=0.05    ; CL=CL/(1.0+ZONE_0_CL*DAMAGE)
ZONE_FRONT_CD=    ; 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_5]								; Wing identifier. A car can have as many wings as necessary.
NAME=R FLOOR								; name of the wing
CHORD=1.70									; length of the wing in meters
SPAN=1.65							; 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,-0.380,-0.3306						; position in x,y,z starting from the CoG
LUT_AOA_CL=wing_RFLOOR_AOA_CL.lut			; Coefficient of Lift lookup table
LUT_GH_CL=wing_RFLOOR_GH_CL.lut								; Height aero lift multiplier lookup table
CL_GAIN=0.5							; Coefficient of Lift multiplier (for easy fine tuning) 
LUT_AOA_CD=empty.lut			; Coefficient of drag lookup table
LUT_GH_CD=empty.lut								; 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    ; 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=-0.350

[WING_6]								; Wing identifier. A car can have as many wings as necessary.
NAME=VENTING								; name of the wing
CHORD=0.5								; length of the wing in meters
SPAN=1.0								; width of the wing in meters. both help determine the frontal area of the wing. Single unit is used to simplify calculations
POSITION=0,0.2,1.4694						; position in x,y,z starting from the CoG
LUT_AOA_CL=wing_vent_AOA_CL.lut			; Coefficient of Lift lookup table
LUT_GH_CL=				; Height aero lift multiplier lookup table
CL_GAIN=1.0									; Coefficient of Lift multiplier (for easy fine tuning) 
LUT_AOA_CD=			; 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
YAW_CL_GAIN=0
ZONE_FRONT_CL=0    ; CL=CL/(1.0+ZONE_0_CL*DAMAGE)
ZONE_FRONT_CD=    ; 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_7]								; Wing identifier. A car can have as many wings as necessary.
NAME=FRONT SPLITTER								; name of the wing
CHORD=0.65								; length of the wing in meters
SPAN=1.50								; width of the wing in meters. both help determine the frontal area of the wing. Single unit is used to simplify calculations
POSITION=0,-0.300,1.9694						; position in x,y,z starting from the CoG
LUT_AOA_CL=wing_ffoils_AOA_CL.lut			; Coefficient of Lift lookup table
LUT_GH_CL=wing_ffoils_GH_CL.lut				; Height aero lift multiplier lookup table
CL_GAIN=1.30									; Coefficient of Lift multiplier (for easy fine tuning) 
LUT_AOA_CD=			; 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
YAW_CL_GAIN=-0.150
ZONE_FRONT_CL=0.05    ; CL=CL/(1.0+ZONE_0_CL*DAMAGE)
ZONE_FRONT_CD=    ; 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)

[FIN_0]
NAME=R FIN							; name of the wing
CHORD=0.35								; length of the wing in meters
SPAN=0.20								; width of the wing in meters. both help determine the frontal area
POSITION=0.0,0.670,-2.0306						; position in x,y,z starting from the CoG
LUT_AOA_CL=empty.lut		; Coefficient of Lift lookup table
LUT_GH_CL=empty.lut							; Height aero lift multiplier lookup table
CL_GAIN=0							; Coefficient of Lift multiplier 
LUT_AOA_CD=wing_fin_R_AOA_CD.lut		; Coefficient of drag lookup table
LUT_GH_CD=empty.lut	; Height aero drag multiplier table
CD_GAIN=2							; 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     ; 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=-0.0

[FIN_1]
NAME=FIN							; name of the wing
CHORD=1.275								; length of the wing in meters
SPAN=1.000								; width of the wing in meters. both help determine the frontal area
POSITION=0,0.00,0.511785 ;1.149285
LUT_AOA_CL=empty.lut		; Coefficient of Lift lookup table
LUT_GH_CL=empty.lut							; Height aero lift multiplier lookup table
CL_GAIN=0							; Coefficient of Lift multiplier 
LUT_AOA_CD=wing_sidedrag.lut		; Coefficient of drag lookup table
LUT_GH_CD=empty.lut							; Height aero drag multiplier table
CD_GAIN=1							; 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     ; 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)

[FIN_2]
NAME=FIN							; name of the wing
CHORD=1.275								; length of the wing in meters
SPAN=1.000								; width of the wing in meters. both help determine the frontal area
POSITION=0,0.00,-0.763215 ;-1.400715
LUT_AOA_CL=empty.lut		; Coefficient of Lift lookup table
LUT_GH_CL=empty.lut							; Height aero lift multiplier lookup table
CL_GAIN=0							; Coefficient of Lift multiplier 
LUT_AOA_CD=wing_sidedrag.lut		; Coefficient of drag lookup table
LUT_GH_CD=empty.lut							; Height aero drag multiplier table
CD_GAIN=1							; 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     ; 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)