[HEADER]
VERSION=2

[WING_0]
NAME=BODY							; name of the wing
CHORD=1.0								; length of the wing in meters
SPAN=1.96								; width of the wing in meters. both help determine the frontal area
POSITION=0,0.45,0.23						; 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=1.5							; 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=1.75							; Coefficient of drag multiplier (for easy fine tuning)
ANGLE=1
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)
YAW_CL_GAIN=-0.0

[WING_1]
NAME=FRONT							; name of the wing
CHORD=0.8								; length of the wing in meters
SPAN=1.96							; width of the wing in meters. both help determine the frontal area
POSITION=0,-0.20,2.00						; 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=1.05							; 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=0.01    ; 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							; name of the wing
CHORD=1.0								; length of the wing in meters
SPAN=1.85							; width of the wing in meters. both help determine the frontal area
POSITION=0,0.95,-2.20						; 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=1.2							; 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=0.01     ; 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)
YAW_CL_GAIN=-0.10

[WING_3]
NAME=DIFFUSER
CHORD=1.0
SPAN=1.865	
POSITION=0,-0.250,-1.80
LUT_AOA_CL=wing_diffuser_AOA_CL.lut
LUT_GH_CL=height_diffuser_CL.lut							; Height aero lift multiplier lookup table
CL_GAIN=1.3
LUT_AOA_CD=wing_diffuser_AOA_CD.lut
LUT_GH_CD=height_diffuser_CD.lut							; Height aero drag multiplier table
CD_GAIN=1.1
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=0.01     ; 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)
YAW_CL_GAIN=-0.10

[WING_4]
NAME=FRONT Right
CHORD=0.2
SPAN=0.25
POSITION=-0.92,0.16,1.83
LUT_AOA_CL=wing_front_AOA_CL.lut
LUT_GH_CL=height_frontwing_CL.lut							; Height aero lift multiplier lookup table
CL_GAIN=0.8
LUT_AOA_CD=wing_front_AOA_CD.lut
LUT_GH_CD=height_frontwing_CD.lut							; Height aero drag multiplier table
CD_GAIN=1.0
ANGLE=14
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=-0.06

[WING_5]
NAME=FRONT Left
CHORD=0.2
SPAN=0.25
POSITION=0.92,0.16,1.83
LUT_AOA_CL=wing_front_AOA_CL.lut
LUT_GH_CL=height_frontwing_CL.lut							; Height aero lift multiplier lookup table
CL_GAIN=0.8
LUT_AOA_CD=wing_front_AOA_CD.lut
LUT_GH_CD=height_frontwing_CD.lut							; Height aero drag multiplier table
CD_GAIN=1.0
ANGLE=14
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=-0.06

[WING_6]
NAME=FENDER_RL
CHORD=0.4
SPAN=0.20
POSITION=0.9342,0.250,-0.75
LUT_AOA_CL=wing_diffuser_AOA_CL.lut
LUT_GH_CL=height_diffuser_rear_CL.lut							; Height aero lift multiplier lookup table
CL_GAIN=0.95896
LUT_AOA_CD=wing_diffuser_AOA_CD.lut
LUT_GH_CD=height_diffuser_rear_CD.lut							; Height aero drag multiplier table
CD_GAIN=1.243
ANGLE=14
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=0.01     ; 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)
YAW_CL_GAIN=-0.10

[WING_7]
NAME=FENDER_RR
CHORD=0.4
SPAN=0.20
POSITION=-0.9342,0.250,-0.75
LUT_AOA_CL=wing_diffuser_AOA_CL.lut
LUT_GH_CL=height_diffuser_rear_CL.lut							; Height aero lift multiplier lookup table
CL_GAIN=0.95896
LUT_AOA_CD=wing_diffuser_AOA_CD.lut
LUT_GH_CD=height_diffuser_rear_CD.lut							; Height aero drag multiplier table
CD_GAIN=1.243
ANGLE=14
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=0.01     ; 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)
YAW_CL_GAIN=-0.10

[WING_8]
NAME=DIFFUSER_2
CHORD=0.65
SPAN=1.865
POSITION=0,0.14,-2.1
LUT_AOA_CL=wing_diffuser_AOA_CL.lut
LUT_GH_CL=						
CL_GAIN=2.0
LUT_AOA_CD=wing_diffuser_AOA_CD.lut
LUT_GH_CD=						
CD_GAIN=0
ANGLE=4
YAW_CL_GAIN=-0.08

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)

