[HEADER]
VERSION=3						; aphidgod xj13 0.2.5

[WING_0]
NAME=BODY							; name of the wing
CHORD=1.0							; length of the wing in meters
SPAN=1.0							; width of the wing in meters. both help determine the frontal area
POSITION=0,0,0							; 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							; 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=1.04							; Coefficient of drag multiplier (for easy fine tuning)
ANGLE=0
YAW_CL_GAIN=-0.0

ZONE_FRONT_CL=0.005    						; CL=CL/(1.0+ZONE_0_CL*DAMAGE)
ZONE_FRONT_CD=0.005    						; CD=CD*(1.0+ZONE_0_CD*DAMAGE)
ZONE_REAR_CL=0.005     						; 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=1.0							; length of the wing in meters
SPAN=1.46							; 1.48 width of the wing in meters. both help determine the frontal area
POSITION=0,-0.10,1.8						; 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=1.09							; Coefficient of Lift multiplier 
LUT_AOA_CD=wing_front_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
YAW_CL_GAIN=0.00

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=0.00     						; CD=CD*(1.0+ZONE_0_CD*DAMAGE)
ZONE_LEFT_CL=0     						; CL=CL/(1.0+ZONE_0_CL*DAMAGE)
ZONE_LEFT_CD=0.0     						; CD=CD*(1.0+ZONE_0_CD*DAMAGE)
ZONE_RIGHT_CL=0     						; CL=CL/(1.0+ZONE_0_CL*DAMAGE)
ZONE_RIGHT_CD=0.0     						; CD=CD*(1.0+ZONE_0_CD*DAMAGE)

[WING_2]
NAME=REAR							; name of the wing
CHORD=1.0							; length of the wing in meters
SPAN=1.56							; width of the wing in meters. both help determine the frontal area
POSITION=0,0.20,-1.35						; 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=1.36							; 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=1.0							; Coefficient of drag multiplier (for easy fine tuning)
ANGLE=0
YAW_CL_GAIN=0.00

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)