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Fabrice Wong Kwok
MUR-AssettoCorsa-19E
Commits
9dbfb143
Commit
9dbfb143
authored
Aug 15, 2020
by
fwongkwok
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changed aero CL properties
parent
6212ca5b
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3 changed files
mur_2019/data/aero.ini
+13
-55
13 additions, 55 deletions
mur_2019/data/aero.ini
mur_2019/data/wing_body_AOA_CD.lut
+12
-5
12 additions, 5 deletions
mur_2019/data/wing_body_AOA_CD.lut
mur_2019/data/wing_body_AOA_CL.lut
+6
-6
6 additions, 6 deletions
mur_2019/data/wing_body_AOA_CL.lut
with
31 additions
and
66 deletions
mur_2019/data/aero.ini
+
13
−
55
View file @
9dbfb143
[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
=
1.0
38
; width of the wing in meters. both help determine the frontal area
POSITION
=
0
.000,0.000,0.00
0 ; 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
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mur_2019/data/wing_body_AOA_CD.lut
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mur_2019/data/wing_body_AOA_CL.lut
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