;Velos.Mods
;http://velosmodsworkshop.com.mx



[HEADER]

VERSION=2


[WING_0]

NAME=BODY							; name of the wing

CHORD=1								; length of the wing in meters

SPAN=1.74							; width of the wing in meters. both help determine the frontal area
POSITION=0,0.3,-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=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=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=0.005                                             ; CD=CD*(1.0+ZONE_0_CD*DAMAGE)

ZONE_REAR_CL=0                                                  ; 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=0.65							; length of the wing in meters

SPAN=1.7							; width of the wing in meters. both help determine the frontal area

POSITION=0,-0.362,2.1						; 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=wing_front_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=2

ZONE_FRONT_CL=0.015                                             ; 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)



[WING_2]

NAME=REAR						        ; name of the wing

CHORD=0.5							; length of the wing in meters

SPAN=1.35							; width of the wing in meters. both help determine the frontal area

POSITION=0,0.39,-1.1						; 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							; 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=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=0.01                                               ; 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)