[HEADER]
VERSION=3

[WING_0]								; Wing identifier. A car can have as many wings as necessary.
NAME=BODY								; name of the wing
CHORD=1									; length of the wing in meters
SPAN=1.67								; width of the wing in meters. both help determine the frontal area of the wing. Single unit is used to simplify calculations
POSITION=0,0.18,-0.10						; 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=0.01    ; CL=CL/(1.0+ZONE_0_CL*DAMAGE)
ZONE_FRONT_CD=0.01    ; CD=CD*(1.0+ZONE_0_CD*DAMAGE)
ZONE_REAR_CL=0.01     ; CL=CL/(1.0+ZONE_0_CL*DAMAGE)
ZONE_REAR_CD=0.01     ; CD=CD*(1.0+ZONE_0_CD*DAMAGE)
ZONE_LEFT_CL=0.01     ; CL=CL/(1.0+ZONE_0_CL*DAMAGE)
ZONE_LEFT_CD=0.01     ; CD=CD*(1.0+ZONE_0_CD*DAMAGE)
ZONE_RIGHT_CL=0.01     ; CL=CL/(1.0+ZONE_0_CL*DAMAGE)
ZONE_RIGHT_CD=0.01     ; CD=CD*(1.0+ZONE_0_CD*DAMAGE)
YAW_CL_GAIN=0.0

[WING_1]
NAME=FRONT
CHORD=1
SPAN=1.67
POSITION=0,-0.250,2.3
LUT_AOA_CL=wing_front_AOA_CL.lut
LUT_GH_CL=height_frontwing_CL.lut							
CL_GAIN=1
LUT_AOA_CD=wing_front_AOA_CD.lut
LUT_GH_CD=height_frontwing_CD.lut			
CD_GAIN=1
ANGLE=0.8
ZONE_FRONT_CL=0.01    ; CL=CL/(1.0+ZONE_0_CL*DAMAGE)
ZONE_FRONT_CD=0.01    ; 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=-0.10

[WING_2]
NAME=REAR
CHORD=1
SPAN=1.67
POSITION=0,0.44,-2.0
LUT_AOA_CL=wing_rear_AOA_CL.lut
LUT_GH_CL=							
CL_GAIN=1
LUT_AOA_CD=wing_rear_AOA_CD.lut
LUT_GH_CD=					
CD_GAIN=1
ANGLE=13
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=0.01     ; 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=-0.15

[WING_3]
NAME=DIFFUSER_F
CHORD=1
SPAN=1.67
POSITION=0,-0.263,1.2
LUT_AOA_CL=wing_diffuser_AOA_CL.lut
LUT_GH_CL=height_diffuser_CL_F.lut							
CL_GAIN=0.33
LUT_AOA_CD=wing_diffuser_AOA_CD.lut
LUT_GH_CD=height_diffuser_CD_F.lut				
CD_GAIN=0
ANGLE=0.8
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=0.01     ; 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=-0.05

[WING_4]
NAME=DIFFUSER_M
CHORD=1
SPAN=1.67
POSITION=0,-0.263,0.2
LUT_AOA_CL=wing_diffuser_AOA_CL.lut
LUT_GH_CL=height_diffuser_CL_M.lut							
CL_GAIN=0.33
LUT_AOA_CD=wing_diffuser_AOA_CD.lut
LUT_GH_CD=height_diffuser_CD_M.lut				
CD_GAIN=0
ANGLE=0.8
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=0.01     ; 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=-0.10

[WING_5]
NAME=DIFFUSER_R
CHORD=1
SPAN=1.67
POSITION=0,-0.263,-0.8
LUT_AOA_CL=wing_diffuser_AOA_CLR.lut
LUT_GH_CL=height_diffuser_CL_R.lut							
CL_GAIN=0.33
LUT_AOA_CD=wing_diffuser_AOA_CDR.lut
LUT_GH_CD=height_diffuser_CD_R.lut				
CD_GAIN=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=0.01     ; CL=CL/(1.0+ZONE_0_CL*DAMAGE)
ZONE_REAR_CD=0.01     ; 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=-0.15


[DYNAMIC_CONTROLLER_0]
WING=5
COMBINATOR=ADD 
INPUT=SPEED_KMH
LUT=wing_controller_speedR.lut
FILTER=0.80
UP_LIMIT=28
DOWN_LIMIT=-1

[DYNAMIC_CONTROLLER_1]
WING=4
COMBINATOR=ADD 
INPUT=SPEED_KMH
LUT=wing_controller_speed.lut
FILTER=0.80
UP_LIMIT=28
DOWN_LIMIT=-1