[HEADER]
VERSION=2

[WING_0]
NAME=BODY							; name of the wing
CHORD=1.175							; length of the wing in meters
SPAN=0.575							; width of the wing in meters. both help determine the frontal area
POSITION=0,0,0						; 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 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=0.005    ; 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_1]
NAME=MID_L							; name of the wing
CHORD=0.65							; length of the wing in meters
SPAN=0.15							; width of the wing in meters. both help determine the frontal area
POSITION=0.5,-0.08,0.07				; 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=0.01							; 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=0							; Coefficient of drag multiplier (for easy fine tuning)
ANGLE=10
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_2]
NAME=MID_R							; name of the wing
CHORD=0.65							; length of the wing in meters
SPAN=0.15							; width of the wing in meters. both help determine the frontal area
POSITION=-0.5,-0.08,0.07				; 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=0.01							; 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=0							; Coefficient of drag multiplier (for easy fine tuning)
ANGLE=10
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_3]
NAME=FRONT							; name of the wing
CHORD=0.65							; length of the wing in meters
SPAN=0.25							; width of the wing in meters. both help determine the frontal area
POSITION=0,0,0.725					; 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=0.01						; 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=0							; Coefficient of drag multiplier (for easy fine tuning)
ANGLE=30
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_4]
NAME=DRIVER_LEAN
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_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_6]
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)

[DYNAMIC_CONTROLLER_0]
WING=4
COMBINATOR=ADD
INPUT=LATG
LUT=wing_body_rl.lut
FILTER=0.90
UP_LIMIT=20
DOWN_LIMIT=0

[DYNAMIC_CONTROLLER_1]
WING=5
COMBINATOR=ADD
INPUT=BRAKE
LUT=wing_brake.lut
FILTER=0.90
UP_LIMIT=20
DOWN_LIMIT=0

[DYNAMIC_CONTROLLER_2]
WING=6
COMBINATOR=ADD
INPUT=GAS
LUT=wing_gas.lut
FILTER=0.90
UP_LIMIT=20
DOWN_LIMIT=0