diff --git a/mur_2019/data/aero.ini b/mur_2019/data/aero.ini index a82b22cc1a5b23341c5a9362430fa4f348963bf2..6cae1e836c38e36f0c3e6fb02f700aab470a8c93 100644 --- a/mur_2019/data/aero.ini +++ b/mur_2019/data/aero.ini @@ -1,18 +1,19 @@ [HEADER] VERSION=3 -[WING_0] -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 -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 -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 + +[WING_0] ; Wing identifier. A car can have as many wings as necessary. +NAME=BODY ; name of the wing +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 (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 ; 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 diff --git a/mur_2019/data/wing_body_AOA_CD.lut b/mur_2019/data/wing_body_AOA_CD.lut index 29ffb3be1c66bc5b4743ef5f81d514eb25bdb28c..01b5a0c16354856cdcf4a60a6fa1336a58129234 100644 --- a/mur_2019/data/wing_body_AOA_CD.lut +++ b/mur_2019/data/wing_body_AOA_CD.lut @@ -1,8 +1,15 @@ -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 diff --git a/mur_2019/data/wing_body_AOA_CL.lut b/mur_2019/data/wing_body_AOA_CL.lut index 7a507e076eeffddcb5665272ee3a7a3d4f24ff08..b7a745acc7a7d31d7c827c749cb6cecb61c9de92 100644 --- a/mur_2019/data/wing_body_AOA_CL.lut +++ b/mur_2019/data/wing_body_AOA_CL.lut @@ -1,7 +1,7 @@ --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