[HEADER]
VERSION=3

[WING_0]
NAME=BODY							; name of the wing
CHORD=1.0								; length of the wing in meters
SPAN=1.90								; width of the wing in meters. both help determine the frontal area
POSITION=0,0.21,0.0						; 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_body_CD.lut							; 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=0.005    ; 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)
YAW_CL_GAIN=-0.0

[WING_1]
NAME=SPLITTER							; name of the wing
CHORD=0.65								; length of the wing in meters
SPAN=2.04							; width of the wing in meters. both help determine the frontal area
POSITION=0,-0.285,2.095						; position in x,y,z starting from the CoG
LUT_AOA_CL=wing_splitter_AOA_CL.lut		; Coefficient of Lift lookup table
LUT_GH_CL=height_splitter_CL.lut							; Height aero lift multiplier lookup table
CL_GAIN=1					; Coefficient of Lift multiplier 
LUT_AOA_CD=wing_splitter_AOA_CD.lut		; Coefficient of drag lookup table
LUT_GH_CD=height_splitter_CD.lut							; Height aero drag multiplier table
CD_GAIN=1							; Coefficient of drag multiplier (for easy fine tuning)
ANGLE=1
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=-0.17

[WING_2]
NAME=FRONT_L							; name of the wing
CHORD=0.50								; length of the wing in meters
SPAN=0.45							; width of the wing in meters. both help determine the frontal area
POSITION=0.275,-0.225,1.91						; 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 
LUT_AOA_CD=wing_front_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=0
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=FRONT_R							; name of the wing
CHORD=0.50								; length of the wing in meters
SPAN=0.45							; width of the wing in meters. both help determine the frontal area
POSITION=-0.275,-0.225,1.91						; 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 
LUT_AOA_CD=wing_front_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=0
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_4]
NAME=REAR							; name of the wing
CHORD=0.6								; length of the wing in meters
SPAN=1.88							; width of the wing in meters. both help determine the frontal area
POSITION=0,0.55,-1.870						; position in x,y,z starting from the CoG
LUT_AOA_CL=wing_rearmovable_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=wing_rearmovable_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=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)
YAW_CL_GAIN=-0.11

[WING_5]
NAME=DIFFUSER
CHORD=1.5
SPAN=1.30
POSITION=0,-0.34, -0.35
LUT_AOA_CL=wing_diffuser_AOA_CL.lut
LUT_GH_CL=height_diffuser_CL.lut							; Height aero lift multiplier lookup table
CL_GAIN=1
LUT_AOA_CD=wing_diffuser_AOA_CD.lut
LUT_GH_CD=height_diffuser_CD.lut            						; Height aero drag multiplier table
CD_GAIN=1
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=-0.10

[DYNAMIC_CONTROLLER_0]
WING=4								; wing number to activate
COMBINATOR=ADD						; COMBINATOR MODE: ADD (value will be added) or MULT (value will be multiplied)
INPUT=BRAKE							; telemetry channel input. LONG LATG BRAKE0-1 GAS0-1 STEER-1+1 SPEED_KMH
LUT=wing_controller_brake.lut		; input data to wing angle lookup table
FILTER=0.99							;
UP_LIMIT=90						; wing angle max limit
DOWN_LIMIT=0						; wing angle min limit

[DYNAMIC_CONTROLLER_1]
WING=4								; wing number to activate
COMBINATOR=ADD						; COMBINATOR MODE: ADD (value will be added) or MULT (value will be multiplied)
INPUT=SPEED_KMH							; telemetry channel input. LONG LATG BRAKE0-1 GAS0-1 STEER-1+1 SPEED_KMH
LUT=wing_controller_speed.lut		; input data to wing angle lookup table
FILTER=0.99							;
UP_LIMIT=90						; wing angle max limit
DOWN_LIMIT=0						; wing angle min limit

[DYNAMIC_CONTROLLER_2]
WING=2								; wing number to activate
COMBINATOR=ADD						; COMBINATOR MODE: ADD (value will be added) or MULT (value will be multiplied)
INPUT=LATG							; telemetry channel input. LONG LATG BRAKE0-1 GAS0-1 STEER-1+1 SPEED_KMH
LUT=wing_controller_latgL.lut		; input data to wing angle lookup table
FILTER=0.99							;
UP_LIMIT=15						; wing angle max limit
DOWN_LIMIT=0						; wing angle min limit

[DYNAMIC_CONTROLLER_3]
WING=3								; wing number to activate
COMBINATOR=ADD						; COMBINATOR MODE: ADD (value will be added) or MULT (value will be multiplied)
INPUT=LATG						; telemetry channel input. LONG LATG BRAKE0-1 GAS0-1 STEER-1+1 SPEED_KMH
LUT=wing_controller_latgR.lut		; input data to wing angle lookup table
FILTER=0.99							;
UP_LIMIT=15						; wing angle max limit
DOWN_LIMIT=0						; wing angle min limit

[DYNAMIC_CONTROLLER_4]
WING=2								; wing number to activate
COMBINATOR=ADD						; COMBINATOR MODE: ADD (value will be added) or MULT (value will be multiplied)
INPUT=SPEED_KMH							; telemetry channel input. LONG LATG BRAKE0-1 GAS0-1 STEER-1+1 SPEED_KMH
LUT=wing_controller_speed2.lut		; input data to wing angle lookup table
FILTER=0.99							;
UP_LIMIT=15						; wing angle max limit
DOWN_LIMIT=0						; wing angle min limit

[DYNAMIC_CONTROLLER_5]
WING=3								; wing number to activate
COMBINATOR=ADD						; COMBINATOR MODE: ADD (value will be added) or MULT (value will be multiplied)
INPUT=SPEED_KMH							; telemetry channel input. LONG LATG BRAKE0-1 GAS0-1 STEER-1+1 SPEED_KMH
LUT=wing_controller_speed2.lut		; input data to wing angle lookup table
FILTER=0.99							;
UP_LIMIT=15						; wing angle max limit
DOWN_LIMIT=0						; wing angle min limit

[DYNAMIC_CONTROLLER_6]
WING=2								; wing number to activate
COMBINATOR=ADD						; COMBINATOR MODE: ADD (value will be added) or MULT (value will be multiplied)
INPUT=BRAKE						; telemetry channel input. LONG LATG BRAKE0-1 GAS0-1 STEER-1+1 SPEED_KMH
LUT=wing_controller_brake2.lut		; input data to wing angle lookup table
FILTER=0.99							;
UP_LIMIT=15						; wing angle max limit
DOWN_LIMIT=0						; wing angle min limit

[DYNAMIC_CONTROLLER_7]
WING=3								; wing number to activate
COMBINATOR=ADD						; COMBINATOR MODE: ADD (value will be added) or MULT (value will be multiplied)
INPUT=BRAKE							; telemetry channel input. LONG LATG BRAKE0-1 GAS0-1 STEER-1+1 SPEED_KMH
LUT=wing_controller_brake2.lut		; input data to wing angle lookup table
FILTER=0.99							;
UP_LIMIT=15						; wing angle max limit
DOWN_LIMIT=0						; wing angle min limit






