public static double SmoothDamp(double current, double target, ref double currentVelocity, double smoothTime, double maxSpeed, double deltaTime)
{
smoothTime = MathD.Max(0.0001d, smoothTime);
double num1 = 2d / smoothTime;
double num2 = num1 * deltaTime;
double num3 = (1.0d / (1.0d + num2 + 0.479999989271164d * num2 * num2 + 0.234999999403954d * num2 * num2 * num2));
double num4 = current - target;
double num5 = target;
double max = maxSpeed * smoothTime;
double num6 = MathD.Clamp(num4, -max, max);
target = current - num6;
double num7 = (currentVelocity + num1 * num6) * deltaTime;
currentVelocity = (currentVelocity - num1 * num7) * num3;
double num8 = target + (num6 + num7) * num3;
if (num5 - current > 0.0 == num8 > num5)
{
num8 = num5;
currentVelocity = (num8 - num5) / deltaTime;
}
return(num8);
}
// This method calculates part values such as mass, lift, drag and connection forces, as well as all intermediates.
public void CalculateAerodynamicValues(bool doInteraction = true)
{
// Calculate intemediate values
//print(part.name + ": Calc Aero values");
b_2 = (double)tipPosition.z - (double)Root.localPosition.z + 1.0;
MAC = ((double)tipScale.x + (double)rootScale.x + 2.0) * (double)modelChordLenght / 2.0;
midChordSweep = (MathD.Rad2Deg * Math.Atan(((double)Root.localPosition.x - (double)tipPosition.x) / b_2));
taperRatio = ((double)tipScale.x + 1.0) / ((double)rootScale.x + 1.0);
surfaceArea = MAC * b_2;
aspectRatio = 2.0 * b_2 / MAC;
ArSweepScale = Math.Pow(aspectRatio / MathD.Cos(MathD.Deg2Rad * midChordSweep), 2.0) + 4.0;
ArSweepScale = 2.0 + Math.Sqrt(ArSweepScale);
ArSweepScale = (2.0 * MathD.PI) / ArSweepScale * aspectRatio;
wingMass = MathD.Clamp((double)massFudgeNumber * surfaceArea * ((ArSweepScale * 2.0) / (3.0 + ArSweepScale)) * ((1.0 + taperRatio) / 2), 0.01, double.MaxValue);
Cd = (double)dragBaseValue / ArSweepScale * (double)dragMultiplier;
Cl = (double)liftFudgeNumber * surfaceArea * ArSweepScale;
//print("Gather Children");
GatherChildrenCl();
connectionForce = MathD.Round(MathD.Clamp(MathD.Sqrt(Cl + ChildrenCl) * (double)connectionFactor, (double)connectionMinimum, double.MaxValue));
// Values always set
if (isWing)
{
wingCost = (float)wingMass * (1f + (float)ArSweepScale / 4f) * costDensity;
wingCost = Mathf.Round(wingCost / 5f) * 5f;
}
else if (isCtrlSrf)
{
wingCost = (float)wingMass * (1f + (float)ArSweepScale / 4f) * costDensity * (1f - modelControlSurfaceFraction);
wingCost += (float)wingMass * (1f + (float)ArSweepScale / 4f) * costDensityControl * modelControlSurfaceFraction;
wingCost = Mathf.Round(wingCost / 5f) * 5f;
}
part.breakingForce = Mathf.Round((float)connectionForce);
part.breakingTorque = Mathf.Round((float)connectionForce);
// Stock-only values
if (!FARactive)
{
// numbers for lift from: http://forum.kerbalspaceprogram.com/threads/118839-Updating-Parts-to-1-0?p=1896409&viewfull=1#post1896409
float stockLiftCoefficient = (float)(surfaceArea / 3.52);
// CoL/P matches CoM unless otherwise specified
part.CoMOffset = new Vector3(Vector3.Dot(Tip.position - Root.position, part.transform.right) / 2, Vector3.Dot(Tip.position - Root.position, part.transform.up) / 2, 0);
if (isWing && !isCtrlSrf)
{
part.Modules.GetModules <ModuleLiftingSurface>().FirstOrDefault().deflectionLiftCoeff = stockLiftCoefficient;
part.mass = stockLiftCoefficient * 0.1f;
}
else
{
ModuleControlSurface mCtrlSrf = part.Modules.OfType <ModuleControlSurface>().FirstOrDefault();
if (mCtrlSrf != null)
{
mCtrlSrf.deflectionLiftCoeff = stockLiftCoefficient;
mCtrlSrf.ctrlSurfaceArea = modelControlSurfaceFraction;
part.mass = stockLiftCoefficient * (1 + modelControlSurfaceFraction) * 0.1f;
}
}
}
// FAR values
// With reflection stuff from r4m0n
if (FARactive)
{
if (part.Modules.Contains("FARControllableSurface"))
{
PartModule FARmodule = part.Modules["FARControllableSurface"];
Type FARtype = FARmodule.GetType();
FARtype.GetField("b_2").SetValue(FARmodule, b_2);
FARtype.GetField("b_2_actual").SetValue(FARmodule, b_2);
FARtype.GetField("MAC").SetValue(FARmodule, MAC);
FARtype.GetField("MAC_actual").SetValue(FARmodule, MAC);
FARtype.GetField("S").SetValue(FARmodule, surfaceArea);
FARtype.GetField("MidChordSweep").SetValue(FARmodule, midChordSweep);
FARtype.GetField("TaperRatio").SetValue(FARmodule, taperRatio);
FARtype.GetField("ctrlSurfFrac").SetValue(FARmodule, modelControlSurfaceFraction);
//print("Set fields");
}
else if (part.Modules.Contains("FARWingAerodynamicModel"))
{
PartModule FARmodule = part.Modules["FARWingAerodynamicModel"];
Type FARtype = FARmodule.GetType();
FARtype.GetField("b_2").SetValue(FARmodule, b_2);
FARtype.GetField("b_2_actual").SetValue(FARmodule, b_2);
FARtype.GetField("MAC").SetValue(FARmodule, MAC);
FARtype.GetField("MAC_actual").SetValue(FARmodule, MAC);
FARtype.GetField("S").SetValue(FARmodule, surfaceArea);
FARtype.GetField("MidChordSweep").SetValue(FARmodule, midChordSweep);
FARtype.GetField("TaperRatio").SetValue(FARmodule, taperRatio);
}
if (!triggerUpdate && doInteraction)
{
TriggerUpdateAllWings();
}
if (doInteraction)
{
triggerUpdate = false;
}
}
//print("FAR Done");
// Update GUI values
if (!FARactive)
{
guiCd = Mathf.Round((float)Cd * 100f) / 100f;
guiCl = Mathf.Round((float)Cl * 100f) / 100f;
guiWingMass = part.mass;
}
guiMAC = (float)MAC;
guiB_2 = (float)b_2;
guiMidChordSweep = (float)midChordSweep;
guiTaperRatio = (float)taperRatio;
guiSurfaceArea = (float)surfaceArea;
guiAspectRatio = (float)aspectRatio;
StartCoroutine(updateAeroDelayed());
}