[HEADER]
VERSION=3

[WING_0]
NAME=BODY							; name of the wing
CHORD=1								; length of the wing in meters
SPAN=1.9							; width of the wing in meters. both help determine the frontal area
POSITION=0,0.0,0.0					; position in x,y,z starting from the CoG
LUT_AOA_CL=							; Coefficient of Lift lookup table
LUT_GH_CL=							; Height aero lift multiplier lookup table
CL_GAIN=							; 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=0.36						; Coefficient of drag multiplier (for easy fine tuning)
ANGLE=0
ZONE_FRONT_CL=-0.005			    ; CL=CL/(1.0+ZONE_0_CL*DAMAGE)
ZONE_FRONT_CD=0.015					; CD=CD*(1.0+ZONE_0_CD*DAMAGE)
ZONE_REAR_CL=-0.005					; CL=CL/(1.0+ZONE_0_CL*DAMAGE)
ZONE_REAR_CD=0.015					; CD=CD*(1.0+ZONE_0_CD*DAMAGE)
ZONE_LEFT_CL=-0.005					; CL=CL/(1.0+ZONE_0_CL*DAMAGE)
ZONE_LEFT_CD=0.01					; CD=CD*(1.0+ZONE_0_CD*DAMAGE)
ZONE_RIGHT_CL=-0.005				; 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						; CL=CL*(1.0+YAW_CL_GAIN*Sin(Yaw))

[WING_1]
NAME=FRONT							; name of the wing
CHORD=1								; length of the wing in meters
SPAN=1.9							; width of the wing in meters. both help determine the frontal area
POSITION=0,-0.393,1.5   			; 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=wing_front_GH_CL.lut		; Height aero lift multiplier lookup table
CL_GAIN=0.29						; Coefficient of Lift multiplier 
LUT_AOA_CD=							; 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=0.005				    ; 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=-0.2					; CL=CL*(1.0+YAW_CL_GAIN*Sin(Yaw))

[WING_2]
NAME=REAR							; name of the wing
CHORD=1 							; length of the wing in meters
SPAN=1.9							; width of the wing in meters. both help determine the frontal area
POSITION=0,0.55,-1.95				; 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=0.09						; 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=0.04						; Coefficient of drag multiplier (for easy fine tuning)
ANGLE=5
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=0.005					; CL=CL/(1.0+ZONE_0_CL*DAMAGE)
ZONE_RIGHT_CD=0.01					; CD=CD*(1.0+ZONE_0_CD*DAMAGE)
YAW_CL_GAIN=-0.9					; CL=CL*(1.0+YAW_CL_GAIN*Sin(Yaw))

[WING_3]
NAME=DIFFUSER						; name of the wing
CHORD=1								; length of the wing in meters
SPAN=1.9							; width of the wing in meters. both help determine the frontal area
POSITION=0,-0.377,-1.55   			; position in x,y,z starting from the CoG
LUT_AOA_CL=wing_diff_AOA_CL.lut		; Coefficient of Lift lookup table
LUT_GH_CL=wing_diff_GH_CL.lut		; Height aero lift multiplier lookup table
CL_GAIN=0.21						; Coefficient of Lift multiplier 
LUT_AOA_CD=							; 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					    ; 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=0.015					; 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=-0.45					; CL=CL*(1.0+YAW_CL_GAIN*Sin(Yaw))

[FIN_0]
NAME=FIN							; name of the wing
CHORD=0.25							; length of the wing in meters
SPAN=0.25							; width of the wing in meters. both help determine the frontal area
POSITION=0,0.55,-1.95				; 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=0.04						; 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=0.85						; 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