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Commit 9dbfb143 authored by fwongkwok's avatar fwongkwok
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changed aero CL properties

parent 6212ca5b
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[HEADER]
VERSION=3
[WING_0]
[WING_0] ; Wing identifier. A car can have as many wings as necessary.
NAME=BODY ; name of the wing
CHORD=1.0 ; length of the wing in meters
SPAN=1.038 ; width of the wing in meters. both help determine the frontal area
POSITION=0.000,0.000,0.000 ; position in x,y,z starting from the CoG
CHORD=1 ; length of the wing in meters
SPAN=1.0 ; width of the wing in meters. both help determine the frontal area of the wing. Single unit is used to simplify calculations
POSITION=0,0.23,0 ; 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=1.0 ; Coefficient of Lift multiplier
CL_GAIN=1.0 ; Coefficient of Lift multiplier (for easy fine tuning)
LUT_AOA_CD=wing_body_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
ANGLE=0 ; Default starting wing angle (degrees)
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)
......@@ -23,46 +24,3 @@ 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
CHORD=1
SPAN=1.038
POSITION=0.000,-0.160,1.400
LUT_AOA_CL=wing_front_AOA_CL.lut
LUT_GH_CL= ; Height aero lift multiplier lookup table
CL_GAIN=1.0
LUT_AOA_CD=wing_front_AOA_CD.lut
LUT_GH_CD= ; Height aero drag multiplier table
CD_GAIN=1.0
ANGLE=6
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=-0.03
[WING_2]
NAME=REAR
CHORD=1
SPAN=1.038
POSITION=0.000,0.600,-0.800
LUT_AOA_CL=wing_rear_AOA_CL.lut
LUT_GH_CL= ; Height aero lift multiplier lookup table
CL_GAIN=1.0
LUT_AOA_CD=wing_rear_AOA_CD.lut
LUT_GH_CD= ; Height aero drag multiplier table
CD_GAIN=1.0
ANGLE=15
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=-0.16
\ No newline at end of file
-10|1
0|0.2
4|0.39
8|0.78
13|1.17
17|1.56
0|0.41
2|0.42
5|0.44
8|0.46
10|0.48
12|0.50
14|0.51
16|0.53
20|0.60
24|0.65
26|0.70
30|1
-10|2.3
0|0.45
4|0.87
8|1.73
13|2.65
17|3.46
-10|0
0|0.0
2|0.0
5|0.0
8|0.0
10|0.0
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