changed more downforce values

mur_2019/data/aero.ini

@@ -6,13 +6,13 @@ VERSION=3
 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
+POSITION=0,0.278,0						; 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) 
+CL_GAIN=6.0								; 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)
+CD_GAIN=6.0								; 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)
@@ -24,3 +24,6 @@ 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
 
+
+
+

mur_2019/data/wing_body_AOA_CD.lut

 -10|1
-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
+0|0.2
+4|0.39
+8|0.78
+13|1.17
+17|1.56
 
 

mur_2019/data/wing_body_AOA_CL.lut

--10|0
-0|0.0
-2|0.0
-5|0.0
-8|0.0
-10|0.0
+-10|2.3
+0|0.45
+4|0.87
+8|1.73
+13|2.65
+17|3.46