[HEADER]
VERSION=2

[WING_0]
NAME=DRAG							; name of the wing
CHORD=1								; length of the wing in meters
SPAN=3.384								; width of the wing in meters. both help determine the frontal area
POSITION=0,-0.080,-0.0						; position in x,y,z starting from the CoG
LUT_AOA_CL=empty.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=0.015    ; CD=CD*(1.0+ZONE_0_CD*DAMAGE)
ZONE_REAR_CL=0     		; CL=CL/(1.0+ZONE_0_CL*DAMAGE)
ZONE_REAR_CD=0.010     ; CD=CD*(1.0+ZONE_0_CD*DAMAGE)
ZONE_LEFT_CL=0     		; CL=CL/(1.0+ZONE_0_CL*DAMAGE)
ZONE_LEFT_CD=0.005     ; CD=CD*(1.0+ZONE_0_CD*DAMAGE)
ZONE_RIGHT_CL=0     	; CL=CL/(1.0+ZONE_0_CL*DAMAGE)
ZONE_RIGHT_CD=0.005     ; CD=CD*(1.0+ZONE_0_CD*DAMAGE)

[WING_1]
NAME=LIFT							; name of the wing
CHORD=1								; length of the wing in meters
SPAN=3.384								; width of the wing in meters. both help determine the frontal area
POSITION=0,-0.080,1.60						; 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 aero lift multiplier lookup table
CL_GAIN=1							; Coefficient of Lift multiplier 
LUT_AOA_CD=empty.lut							; Coefficient of drag lookup table
LUT_GH_CD=							; Height aero drag multiplier table
CD_GAIN=0							; Coefficient of drag multiplier (for easy fine tuning)
ANGLE=0
ZONE_FRONT_CL=0.010     ; CL=CL/(1.0+ZONE_0_CL*DAMAGE)
ZONE_FRONT_CD=0    		; CD=CD*(1.0+ZONE_0_CD*DAMAGE)
ZONE_REAR_CL=0.005     ; CL=CL/(1.0+ZONE_0_CL*DAMAGE)
ZONE_REAR_CD=0     		; CD=CD*(1.0+ZONE_0_CD*DAMAGE)
ZONE_LEFT_CL=0.002     ; CL=CL/(1.0+ZONE_0_CL*DAMAGE)
ZONE_LEFT_CD=0    		; CD=CD*(1.0+ZONE_0_CD*DAMAGE)
ZONE_RIGHT_CL=0.002     ; CL=CL/(1.0+ZONE_0_CL*DAMAGE)
ZONE_RIGHT_CD=0     	; CD=CD*(1.0+ZONE_0_CD*DAMAGE)

[FIN_0]
NAME=FIN							; name of the wing
CHORD=1.000								; length of the wing in meters
SPAN=1.000								; width of the wing in meters. both help determine the frontal area
POSITION=0,0.360,-0.800						; 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






[WING_2]
NAME=Light Bar
CHORD=0.18
SPAN=1.0
POSITION=0,1.300,0.220
LUT_AOA_CL=empty.lut
LUT_GH_CL=
CL_GAIN=0.0
LUT_AOA_CD=box.lut
LUT_GH_CD=
CD_GAIN=1.0
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

[WING_3]
NAME=Stopwatch
CHORD=0.18
SPAN=1.0
POSITION=0,1.300,0.220
LUT_AOA_CL=empty.lut
LUT_GH_CL=
CL_GAIN=0.0
LUT_AOA_CD=empty.lut
LUT_GH_CD=
CD_GAIN=0.0
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