[HEADER]
VERSION=3

[WING_0]
NAME=BODY							; name of the wing
CHORD=1								; length of the wing in meters
SPAN=1.80								; width of the wing in meters. both help determine the frontal area
POSITION=0,0.15,-0.060						; 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=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=0.0

[WING_1]
NAME=FRONT							; name of the wing
CHORD=1								; length of the wing in meters
SPAN=1.80							; width of the wing in meters. both help determine the frontal area
POSITION=0,-0.220,2.400						; 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=1.80						; 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=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)
YAW_CL_GAIN=-0.12

[WING_2]
NAME=REAR							; name of the wing
CHORD=1.0								; length of the wing in meters
SPAN=1.80							; width of the wing in meters. both help determine the frontal area
POSITION=0,0.64,-1.750						; 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=1.70						; 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=6
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=-0.16

[WING_3]
NAME=DIFFUSERF
CHORD=1.0
SPAN=1.80
POSITION=0,-0.230, 1.200
LUT_AOA_CL=wing_diffuser_AOA_CL.lut
LUT_GH_CL=height_diffuser_CL.lut							; Height aero lift multiplier lookup table
CL_GAIN=0.33
LUT_AOA_CD=wing_diffuser_AOA_CD.lut
LUT_GH_CD=							; Height aero drag multiplier table
CD_GAIN=0.33
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=-0.15

[WING_4]
NAME=DIFFUSERM
CHORD=1.0
SPAN=1.80
POSITION=0,-0.230, 0.100
LUT_AOA_CL=wing_diffuser_AOA_CL.lut
LUT_GH_CL=height_diffuser_CL.lut							; Height aero lift multiplier lookup table
CL_GAIN=0.30
LUT_AOA_CD=wing_diffuser_AOA_CD.lut
LUT_GH_CD=							; Height aero drag multiplier table
CD_GAIN=0.33
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=-0.18

[WING_5]
NAME=DIFFUSERR
CHORD=1.0
SPAN=1.80
POSITION=0,-0.230, -0.900
LUT_AOA_CL=wing_diffuser_AOA_CL.lut
LUT_GH_CL=height_diffuser_CL.lut							; Height aero lift multiplier lookup table
CL_GAIN=0.60
LUT_AOA_CD=wing_diffuser_AOA_CD.lut
LUT_GH_CD=							; Height aero drag multiplier table
CD_GAIN=0.33
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=-0.20

[FIN_0]
NAME=FIN							; name of the wing
CHORD=1.0								; length of the wing in meters
SPAN=1.0								; width of the wing in meters. both help determine the frontal area
POSITION=0,0.25,-1.800						; 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=1.0							; 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=3
COMBINATOR=ADD 
INPUT=SPEED_KMH
LUT=wing_controller_speed_f.lut
FILTER=0.80
UP_LIMIT=20
DOWN_LIMIT=-1

[DYNAMIC_CONTROLLER_1]
WING=4
COMBINATOR=ADD 
INPUT=SPEED_KMH
LUT=wing_controller_speed_m.lut
FILTER=0.80
UP_LIMIT=20
DOWN_LIMIT=-1

[DYNAMIC_CONTROLLER_2]
WING=5
COMBINATOR=ADD 
INPUT=SPEED_KMH
LUT=wing_controller_speed_r.lut
FILTER=0.80
UP_LIMIT=20
DOWN_LIMIT=-1