[HEADER]
VERSION=3

[WING_0]
NAME=BODY							; name of the wing
CHORD=1.0								; length of the wing in meters
SPAN=1.94								; width of the wing in meters. both help determine the frontal area
POSITION=0,0.28,0.600						; 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)
YAW_CL_GAIN=0

[WING_1]
NAME=FRONT							; name of the wing
CHORD=1								; length of the wing in meters
SPAN=1.94							; width of the wing in meters. both help determine the frontal area
POSITION=0,-0.30,2.300						; 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=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=-0.10

[WING_2]
NAME=REAR_R							; name of the wing
CHORD=1.0								; length of the wing in meters
SPAN=0.97							; width of the wing in meters. both help determine the frontal area
POSITION=-0.485,0.60,-1.600						; 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							; 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							; 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=-0.10

[WING_3]
NAME=REAR_L							; name of the wing
CHORD=1.0								; length of the wing in meters
SPAN=0.97							; width of the wing in meters. both help determine the frontal area
POSITION=0.485,0.60,-1.600						; 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							; 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							; 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=-0.10

[WING_4]
NAME=DIFFUSER
CHORD=1.0
SPAN=1.94
POSITION=0,-0.31, -0.350
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=1.0
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=0.0    ; 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=-0.12


; steer 


[DYNAMIC_CONTROLLER_0]
WING=2
COMBINATOR=ADD 
INPUT=LATG
LUT=wingrear_right_steerleft.lut
FILTER=0.97
UP_LIMIT=10
DOWN_LIMIT=1

[DYNAMIC_CONTROLLER_1]
WING=3
COMBINATOR=ADD 
INPUT=LATG
LUT=wingrear_left_steerleft.lut
FILTER=0.97
UP_LIMIT=10
DOWN_LIMIT=1

[DYNAMIC_CONTROLLER_2]
WING=1
COMBINATOR=ADD 
INPUT=LATG
LUT=wing_front_steer.lut
FILTER=0.97
UP_LIMIT=10
DOWN_LIMIT=1

;gas

[DYNAMIC_CONTROLLER_3]
WING=1
COMBINATOR=MULT 
INPUT=GAS
LUT=wing_front_gas.lut
FILTER=0.99
UP_LIMIT=10
DOWN_LIMIT=1

[DYNAMIC_CONTROLLER_4]
WING=2
COMBINATOR=MULT 
INPUT=GAS
LUT=wingrear_right_gas.lut
FILTER=0.978
UP_LIMIT=10
DOWN_LIMIT=1

[DYNAMIC_CONTROLLER_5]
WING=3
COMBINATOR=MULT 
INPUT=GAS
LUT=wingrear_left_gas.lut
FILTER=0.978
UP_LIMIT=10
DOWN_LIMIT=1


;brake

[DYNAMIC_CONTROLLER_6]
WING=1
COMBINATOR=ADD 
INPUT=BRAKE
LUT=wing_front_brake.lut
FILTER=0.97
UP_LIMIT=10
DOWN_LIMIT=1

[DYNAMIC_CONTROLLER_7]
WING=2
COMBINATOR=ADD 
INPUT=BRAKE
LUT=wingrear_right.lut
FILTER=0.97
UP_LIMIT=10
DOWN_LIMIT=1

[DYNAMIC_CONTROLLER_8]
WING=3
COMBINATOR=ADD 
INPUT=BRAKE
LUT=wingrear_left.lut
FILTER=0.97
UP_LIMIT=10
DOWN_LIMIT=1




