[HEADER]
VERSION=2


[WING_0]
NAME=BODY							; name of the wing
CHORD=1								; length of the wing in meters
SPAN=1.3								; width of the wing in meters. both help determine the frontal area
POSITION=0,0.10,-0.05						; 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=1.0							; 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=0.01     ; 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
CHORD=1
SPAN=1.5
POSITION=0,-0.22,2.25
LUT_AOA_CL=wing_front_AOA_CL.lut
LUT_GH_CL=height_frontwing_CL.lut							; Height aero lift multiplier lookup table
CL_GAIN=1.30
LUT_AOA_CD=wing_front_AOA_CD.lut
LUT_GH_CD=height_frontwing_CD.lut							; Height aero drag multiplier table
CD_GAIN=1.00
ANGLE=6
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)

[WING_2]
NAME=REAR
CHORD=1
SPAN=1.5
POSITION=0,0.5,-1.800
LUT_AOA_CL=wing_rear_AOA_CL.lut
LUT_GH_CL=							; Height aero lift multiplier lookup table
CL_GAIN=1.50
LUT_AOA_CD=wing_rear_AOA_CD.lut
LUT_GH_CD=							; Height aero drag multiplier table
CD_GAIN=1.00
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=0.01     ; 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
SPAN=1.5
POSITION=0,-0.25, -0.150
LUT_AOA_CL=wing_diffuser_AOA_CL.lut
LUT_GH_CL=height_diffuser_CL.lut							; Height aero lift multiplier lookup table
CL_GAIN=1.50
LUT_AOA_CD=wing_diffuser_AOA_CD.lut
LUT_GH_CD=height_diffuser_CD.lut							; Height aero drag multiplier table
CD_GAIN=0
ANGLE=1
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=0.0    ; CL=CL/(1.0+ZONE_0_CL*DAMAGE)
ZONE_REAR_CD=0.0     ; CD=CD*(1.0+ZONE_0_CD*DAMAGE)
ZONE_LEFT_CL=0.01     ; CL=CL/(1.0+ZONE_0_CL*DAMAGE)
ZONE_LEFT_CD=0.01     ; CD=CD*(1.0+ZONE_0_CD*DAMAGE)
ZONE_RIGHT_CL=0.01     ; CL=CL/(1.0+ZONE_0_CL*DAMAGE)
ZONE_RIGHT_CD=0.01     ; CD=CD*(1.0+ZONE_0_CD*DAMAGE)

[WING_4]
NAME=FAN
CHORD=1
SPAN=1.5
POSITION=0,-1.25, -0.120
LUT_AOA_CL=wing_fan_AOA_CL.lut
LUT_GH_CL=height_fan_CL.lut							; Height aero lift multiplier lookup table
CL_GAIN=1.00
LUT_AOA_CD=
LUT_GH_CD=							; Height aero drag multiplier table
CD_GAIN=0
ANGLE=1
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=0.0    ; CL=CL/(1.0+ZONE_0_CL*DAMAGE)
ZONE_REAR_CD=0.0     ; CD=CD*(1.0+ZONE_0_CD*DAMAGE)
ZONE_LEFT_CL=0.01     ; CL=CL/(1.0+ZONE_0_CL*DAMAGE)
ZONE_LEFT_CD=0.01     ; CD=CD*(1.0+ZONE_0_CD*DAMAGE)
ZONE_RIGHT_CL=0.01     ; 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=MULT
INPUT=SPEED_KMH
LUT=wing_controller_speed.lut
FILTER=0.99
UP_LIMIT=10
DOWN_LIMIT=0