[HEADER]
VERSION=2



[WING_0]

NAME=BODY							; name of the wing

CHORD=1								; length of the wing in meters

SPAN=2.20								; width of the wing in meters. both help determine the frontal area

POSITION=0,0.18,-0.10						; 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=0.65							; 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=FRONT							; name of the wing

CHORD=1								; length of the wing in meters

SPAN=2.20							; width of the wing in meters. both help determine the frontal area

POSITION=0,-0.205,1.9500						; 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=0.65							; Coefficient of drag multiplier (for easy fine tuning)

ANGLE=3

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=2.20								; width of the wing in meters. both help determine the frontal area

POSITION=0,0.74,-1.800						; 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=0.65							; 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)


[WING_3]

NAME=DIFFUSER
CHORD=1.0

SPAN=2.20	

POSITION=0,-0.25, -1.5

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=0.65
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)


[WING_4]

NAME=FRONT2							; name of the wing

CHORD=1.5								; length of the wing in meters

SPAN=2.20							; 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=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=0.65							; Coefficient of drag multiplier (for easy fine tuning)

ANGLE=5

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)


[DYNAMIC_CONTROLLER_0]

WING=3

COMBINATOR=ADD 
INPUT=SPEED_KMH

LUT=wing_controller_speed.lut

FILTER=0.80

UP_LIMIT=14
DOWN_LIMIT=0