[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=0,0.0401,0.201				; 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=1.2					; 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,-0.1001,1.601				; 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=0,0.3501,-1.701				; 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)


; ;|||||||||||||||||DIFFUSER||||||||||||||||||||

; [WING_3]
; NAME=DIFFUSER
; CHORD=2.15
; SPAN=1.0	
; POSITION=0,-0.27, 0
; LUT_AOA_CL=wing_diffuser_AOA_CL.lut
; LUT_GH_CL=							; Height aero lift multiplier lookup table
; CL_GAIN=1.0
; LUT_AOA_CD=wing_diffuser_AOA_CD.lut
; LUT_GH_CD=							; Height aero drag multiplier table
; CD_GAIN=1.0
; 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=-0.00

; [DYNAMIC_CONTROLLER_0]
; WING=0
; COMBINATOR=ADD 
; INPUT=SPEED_KMH
; LUT=wing_controller_speed.lut
; FILTER=0.80
; UP_LIMIT=12
; DOWN_LIMIT=0