[HEADER]
VERSION=3

[WING_0]
NAME=BODY							; name of the wing
CHORD=1								; length of the wing in meters
SPAN=1.5882								; width of the wing in meters. both help determine the frontal area
POSITION=0,0.15,-0.08						; 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=1							; Coefficient of drag multiplier (for easy fine tuning)
ANGLE=2
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=0.01     ; 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)
YAW_CL_GAIN=-0.0

[WING_1]
NAME=FRONT Right
CHORD=1
SPAN=0.7941
POSITION=-0.49,-0.17,2.70
LUT_AOA_CL=wing_front_AOA_CL.lut
LUT_GH_CL=height_frontwing_CL.lut							; Height aero lift multiplier lookup table
CL_GAIN=0.973
LUT_AOA_CD=wing_front_AOA_CD.lut
LUT_GH_CD=height_frontwing_CD.lut							; Height aero drag multiplier table
CD_GAIN=1.0
ANGLE=25
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=-0.06

[WING_2]
NAME=FRONT Left
CHORD=1
SPAN=0.7941
POSITION=0.49,-0.17,2.70
LUT_AOA_CL=wing_front_AOA_CL.lut
LUT_GH_CL=height_frontwing_CL.lut							; Height aero lift multiplier lookup table
CL_GAIN=0.973
LUT_AOA_CD=wing_front_AOA_CD.lut
LUT_GH_CD=height_frontwing_CD.lut							; Height aero drag multiplier table
CD_GAIN=1.0
ANGLE=25
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=-0.06


[WING_3]
NAME=REAR
CHORD=1
SPAN=1.5882
POSITION=0,0.55,-1.700
LUT_AOA_CL=wing_rear_AOA_CL.lut
LUT_GH_CL=							; Height aero lift multiplier lookup table
CL_GAIN=0.8
LUT_AOA_CD=wing_rear_AOA_CD.lut
LUT_GH_CD=							; Height aero drag multiplier table
CD_GAIN=1.1
ANGLE=25
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=0.007

[WING_4]
NAME=DIFF_Front
CHORD=1
SPAN=1.5882
POSITION=0,-0.20,0.10
LUT_AOA_CL=wing_diffuser_AOA_CL.lut
LUT_GH_CL=height_diffuser_CL.lut							; Height aero lift multiplier lookup table
CL_GAIN=0.531
LUT_AOA_CD=wing_diffuser_AOA_CD.lut
LUT_GH_CD=height_diffuser_CD.lut							; Height aero drag multiplier table
CD_GAIN=0
ANGLE=3.5
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=0.0    ; CL=CL/(1.0+ZONE_0_CL*DAMAGE)
ZONE_REAR_CD=0.0     ; CD=CD*(1.0+ZONE_0_CD*DAMAGE)
ZONE_LEFT_CL=0.01     ; 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=-0.09

[WING_5]
NAME=DIFFUSER_RL
CHORD=1
SPAN=0.7941
POSITION=-0.3423,-0.165,-1.32
LUT_AOA_CL=wing_diffuser_AOA_CL.lut
LUT_GH_CL=height_diffuser_rear_CL.lut							; Height aero lift multiplier lookup table
CL_GAIN=0.548
LUT_AOA_CD=wing_diffuser_AOA_CD.lut
LUT_GH_CD=height_diffuser_rear_CD.lut							; Height aero drag multiplier table
CD_GAIN=1.043
ANGLE=3.5
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=0.01     ; 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=-0.10

[WING_6]
NAME=DIFFUSER_RR
CHORD=1
SPAN=0.7941
POSITION=0.3342,-0.165,-1.32
LUT_AOA_CL=wing_diffuser_AOA_CL.lut
LUT_GH_CL=height_diffuser_rear_CL.lut							; Height aero lift multiplier lookup table
CL_GAIN=0.548
LUT_AOA_CD=wing_diffuser_AOA_CD.lut
LUT_GH_CD=height_diffuser_rear_CD.lut							; Height aero drag multiplier table
CD_GAIN=1.043
ANGLE=3.5
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=0.01     ; 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=-0.10

[WING_7]
NAME=DRS
CHORD=1
SPAN=1.5882
POSITION=0,0.59,-1.800
LUT_AOA_CL=wing_rear2_AOA_CL.lut
LUT_GH_CL=							; Height aero lift multiplier lookup table
CL_GAIN=1.0
LUT_AOA_CD=wing_rear2_AOA_CD.lut
LUT_GH_CD=							; Height aero drag multiplier table
CD_GAIN=1.0
ANGLE=15
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=-0.04

[WING_8]
NAME=Monkeyseat
CHORD=1
SPAN=1.5882
POSITION=0,0.15,-1.800
LUT_AOA_CL=wing_monkey_AOA_CL.lut
LUT_GH_CL=							; Height aero lift multiplier lookup table
CL_GAIN=1.0
LUT_AOA_CD=wing_monkey_AOA_CD.lut
LUT_GH_CD=							; Height aero drag multiplier table
CD_GAIN=1.0
ANGLE=10
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_9]
NAME=HALO
CHORD=0.1
SPAN=0.1
POSITION=0, -0.250, 1.800
LUT_AOA_CL=halo.lut
LUT_GH_CL=halo.lut
CL_GAIN=0.0
LUT_AOA_CD=halo.lut
LUT_GH_CD=halo.lut
CD_GAIN=0.0
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=-0.0

[FIN_0]
NAME=FIN							; name of the wing
CHORD=1.6								; length of the wing in meters
SPAN=0.50								; width of the wing in meters. both help determine the frontal area
POSITION=0,0.50,-0.780						; 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

[FIN_1]
NAME=FIN							; name of the wing
CHORD=0.5								; length of the wing in meters
SPAN=0.50								; width of the wing in meters. both help determine the frontal area
POSITION=0,0.35,-2.050						; 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=4									; wing number to activate
COMBINATOR=MULT 							; COMBINATOR MODE: ADD or MULT
INPUT=STEER						; telemetry channel input. LONG LATG BRAKE0-1 GAS0-1 STEER-1+1 SPEED
LUT=wing_controller_steer_diff_FR.lut			; input data to wing angle lookup table
FILTER=0.99								; filter for eliminating spikes in movement
UP_LIMIT=30								; wing angle max limit
DOWN_LIMIT=0							; wing angle min limit

[DYNAMIC_CONTROLLER_1]
WING=5
COMBINATOR=ADD 
INPUT=SPEED_KMH
LUT=wing_controller_speed.lut
FILTER=0.80
UP_LIMIT=12
DOWN_LIMIT=0

[DYNAMIC_CONTROLLER_2]
WING=6
COMBINATOR=ADD 
INPUT=SPEED_KMH
LUT=wing_controller_speed.lut
FILTER=0.80
UP_LIMIT=12
DOWN_LIMIT=0

[DYNAMIC_CONTROLLER_3]
WING=8
COMBINATOR=MULT 
INPUT=GAS
LUT=wing_controller_gas.lut
FILTER=0.80
UP_LIMIT=15
DOWN_LIMIT=0

[DYNAMIC_CONTROLLER_4]
WING=3
COMBINATOR=MULT 
INPUT=GAS
LUT=wing_controller_gasRW.lut
FILTER=0.80
UP_LIMIT=30
DOWN_LIMIT=0


[DYNAMIC_CONTROLLER_5]
WING=1
COMBINATOR=MULT 
INPUT=SPEED_KMH
LUT=wing_controller_highspeed.lut
FILTER=0.80
UP_LIMIT=30
DOWN_LIMIT=0

[DYNAMIC_CONTROLLER_6]
WING=2
COMBINATOR=MULT 
INPUT=SPEED_KMH
LUT=wing_controller_highspeed.lut
FILTER=0.80
UP_LIMIT=30
DOWN_LIMIT=0

[DYNAMIC_CONTROLLER_7]
WING=3
COMBINATOR=MULT 
INPUT=SPEED_KMH
LUT=wing_controller_highspeed.lut
FILTER=0.80
UP_LIMIT=30
DOWN_LIMIT=0

