[HEADER]
VERSION=3

[WING_0]
NAME=BODY							; name of the wing
CHORD=1								; length of the wing in meters
SPAN=1.6504								; width of the wing in meters. both help determine the frontal area
POSITION=0,0.21,-0.061						; 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 
LUT_AOA_CD=wing_body_AOA_CD.lut		; Coefficient of drag lookup table
LUT_GH_CD=	; Height aero drag multiplier table
CD_GAIN=0.83							; 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=0.006    ; CD=CD*(1.0+ZONE_0_CD*DAMAGE)
ZONE_REAR_CL=0     ; CL=CL/(1.0+ZONE_0_CL*DAMAGE)
ZONE_REAR_CD=0.006     ; CD=CD*(1.0+ZONE_0_CD*DAMAGE)
ZONE_LEFT_CL=0     ; CL=CL/(1.0+ZONE_0_CL*DAMAGE)
ZONE_LEFT_CD=0.02     ; CD=CD*(1.0+ZONE_0_CD*DAMAGE)
ZONE_RIGHT_CL=0     ; CL=CL/(1.0+ZONE_0_CL*DAMAGE)
ZONE_RIGHT_CD=0.02     ; CD=CD*(1.0+ZONE_0_CD*DAMAGE)
YAW_CL_GAIN=-0.0

[WING_1]
NAME=FRONT							; name of the wing
CHORD=1								; length of the wing in meters
SPAN=1.6504							; width of the wing in meters. both help determine the frontal area
POSITION=0,-0.206,2.101						; 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_front_CL.lut							; Height aero lift multiplier lookup table
CL_GAIN=1.0							; Coefficient of Lift multiplier 
LUT_AOA_CD=wing_front_AOA_CD.lut		; Coefficient of drag lookup table
LUT_GH_CD=height_front_CD.lut							; Height aero drag multiplier table
CD_GAIN=1.0							; Coefficient of drag multiplier (for easy fine tuning)
ANGLE=4
ZONE_FRONT_CL=0.016    ; CL=CL/(1.0+ZONE_0_CL*DAMAGE)
ZONE_FRONT_CD=0.016    ; 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=-0.07

[WING_2]
NAME=REAR							; name of the wing
CHORD=1.0								; length of the wing in meters
SPAN=1.6504							; width of the wing in meters. both help determine the frontal area
POSITION=0,0.61,-1.801						; 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=1.0							; Coefficient of Lift multiplier 
LUT_AOA_CD=wing_rear_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=4
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=0.011    ; CL=CL/(1.0+ZONE_0_CL*DAMAGE)
ZONE_REAR_CD=0.016     ; 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=-0.051

[WING_3]
NAME=DIFFUSER
CHORD=1.0
SPAN=1.6504
POSITION=0,-0.206, -0.501
LUT_AOA_CL=wing_diffuser_AOA_CL.lut
LUT_GH_CL=height_diffuser_CL.lut							; Height aero lift multiplier lookup table
CL_GAIN=0.98
LUT_AOA_CD=wing_diffuser_AOA_CD.lut
LUT_GH_CD=height_diffuser_CD.lut							; Height aero drag multiplier table
CD_GAIN=1.04
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=0.0    ; CL=CL/(1.0+ZONE_0_CL*DAMAGE)
ZONE_REAR_CD=0.0     ; 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=-0.061

[WING_4]
NAME=DRIVER_BRAKE
CHORD=1
SPAN=1.0
POSITION=0,0,0
LUT_AOA_CL=empty.lut
LUT_GH_CL=                      
CL_GAIN=0.0
LUT_AOA_CD=empty.lut
LUT_GH_CD=                     
CD_GAIN=0.0
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_5]
NAME=DRIVER_GAS
CHORD=1
SPAN=1.0
POSITION=0,0,0
LUT_AOA_CL=empty.lut
LUT_GH_CL=                      
CL_GAIN=0.0
LUT_AOA_CD=empty.lut
LUT_GH_CD=                     
CD_GAIN=0.0
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)

[FIN_0]
NAME=FIN							; name of the wing
CHORD=1.701								; length of the wing in meters
SPAN=0.501								; width of the wing in meters. both help determine the frontal area
POSITION=0,0.501,-1.061						; position in x,y,z starting from the CoG
LUT_AOA_CL=fin_AOA_CL.lut		; Coefficient of Lift lookup table
LUT_GH_CL=							; Height aero lift multiplier lookup table
CL_GAIN=1							; Coefficient of Lift multiplier 
LUT_AOA_CD=fin_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
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


[DYNAMIC_CONTROLLER_0]
WING=3
COMBINATOR=ADD 
INPUT=SPEED_KMH
LUT=wing_controller_speed.lut
FILTER=0.80
UP_LIMIT=25
DOWN_LIMIT=0

[DYNAMIC_CONTROLLER_1]
WING=2
COMBINATOR=MULT 
INPUT=SPEED_KMH
LUT=wing_controller_speed_r.lut
FILTER=0.80
UP_LIMIT=25
DOWN_LIMIT=0

[DYNAMIC_CONTROLLER_2]
WING=4
COMBINATOR=ADD
INPUT=BRAKE
LUT=wing_brake.lut
FILTER=0.90
UP_LIMIT=20
DOWN_LIMIT=0

[DYNAMIC_CONTROLLER_3]
WING=5
COMBINATOR=ADD
INPUT=GAS
LUT=wing_gas.lut
FILTER=0.90
UP_LIMIT=20
DOWN_LIMIT=0