[HEADER]
VERSION=2

[WING_0]
NAME=BODY
CHORD=1.0
SPAN=1.7
POSITION=0,0.15,0.0
LUT_AOA_CL=wing_body_AOA_CL.lut
LUT_GH_CL=
CL_GAIN=1
LUT_AOA_CD=wing_body_AOA_CD.lut
LUT_GH_CD=
CD_GAIN=1
ANGLE=0
ZONE_FRONT_CL=0
ZONE_FRONT_CD=0.005
ZONE_REAR_CL=0
ZONE_REAR_CD=0.005
ZONE_LEFT_CL=0
ZONE_LEFT_CD=0.01
ZONE_RIGHT_CL=0
ZONE_RIGHT_CD=0.01

[WING_1]
NAME=FRONT							; name of the wing
CHORD=1								; length of the wing in meters
SPAN=1.8							; width of the wing in meters. both help determine the frontal area
POSITION=0,-0.24 ,1.92						; 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=2
ZONE_FRONT_CL=0.015    ; CL=CL/(1.0+ZONE_0_CL*DAMAGE)
ZONE_FRONT_CD=0.015    ; 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)

[WING_2]
NAME=REAR							; name of the wing
CHORD=1								; length of the wing in meters
SPAN=1.8								; width of the wing in meters. both help determine the frontal area
POSITION=0,0.41,-1.650						; 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=12
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=-0.10

[WING_3]
NAME=DIFFUSER
CHORD=1
SPAN=1.12	
POSITION=0,-0.250, -1.400
LUT_AOA_CL=wing_diffuser_AOA_CL.lut
LUT_GH_CL=height_diffuser_CL.lut							; Height aero lift multiplier lookup table
CL_GAIN=1.0
LUT_AOA_CD=wing_diffuser_AOA_CD.lut
LUT_GH_CD=height_diffuser_CD.lut							; 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=-0.05

[DYNAMIC_CONTROLLER_0]
WING=2
COMBINATOR=MULT 
INPUT=SPEED_KMH
LUT=wing_controller_speed.lut
FILTER=0.995
UP_LIMIT=7
DOWN_LIMIT=0

[DYNAMIC_CONTROLLER_1]
WING=2
COMBINATOR=ADD
INPUT=BRAKE
LUT=wing_controller_brake.lut
FILTER=0.995
UP_LIMIT=15
DOWN_LIMIT=0

