private void UpdateUpstreamValuesFromWingModules(List <FARWingAerodynamicModel> wingModules, List <double> associatedInfluences, double directionalInfluence, double thisWingAoA)
{
for (int i = 0; i < wingModules.Count; i++)
{
FARWingAerodynamicModel wingModule = wingModules[i];
double wingInfluenceFactor = associatedInfluences[i] * directionalInfluence;
double tmp = Vector3.Dot(wingModule.transform.forward, parentWingModule.transform.forward);
effectiveUpstreamMAC += wingModule.GetMAC() * wingInfluenceFactor;
effectiveUpstreamb_2 += wingModule.Getb_2() * wingInfluenceFactor;
effectiveUpstreamArea += wingModule.S * wingInfluenceFactor;
effectiveUpstreamLiftSlope += wingModule.GetLiftSlope() * wingInfluenceFactor;
effectiveUpstreamStall += wingModule.GetStall() * wingInfluenceFactor;
effectiveUpstreamCosSweepAngle += wingModule.GetCosSweepAngle() * wingInfluenceFactor;
effectiveUpstreamAoAMax += wingModule.AoAmax * wingInfluenceFactor;
effectiveUpstreamCd0 += wingModule.GetCd0() * wingInfluenceFactor;
effectiveUpstreamInfluence += wingInfluenceFactor;
double wAoA = wingModule.CalculateAoA(wingModule.GetVelocity()) * Math.Sign(tmp);
tmp = (thisWingAoA - wAoA) * wingInfluenceFactor; //First, make sure that the AoA are wrt the same direction; then account for any strange angling of the part that shouldn't be there
effectiveUpstreamAoA += tmp;
}
}
//Returns the tinted color if active; else it returns an alpha 0 color
private Color AeroVisualizationTintingCalculation(AeroVisualizationGUI aeroVizGUI)
{
// Disable tinting for low dynamic pressure to prevent flicker
if (vessel.dynamicPressurekPa <= 0.00001)
{
return(new Color(0, 0, 0, 0));
}
// Stall tinting overrides Cl / Cd tinting
if (legacyWingModel != null && aeroVizGUI.TintForStall)
{
return(new Color((float)((legacyWingModel.GetStall() * 100.0) / aeroVizGUI.FullySaturatedStall), 0f, 0f, 0.5f));
}
if (!aeroVizGUI.TintForCl && !aeroVizGUI.TintForCd)
{
return(new Color(0, 0, 0, 0));
}
double visualizationCl = 0, visualizationCd = 0;
if (projectedArea.totalArea > 0.0)
{
Vector3 worldVelNorm = partTransform.localToWorldMatrix.MultiplyVector(partLocalVelNorm);
Vector3 worldDragArrow = Vector3.Dot(totalWorldSpaceAeroForce, worldVelNorm) * worldVelNorm;
Vector3 worldLiftArrow = totalWorldSpaceAeroForce - worldDragArrow;
double invAndDynPresArea = legacyWingModel != null ? legacyWingModel.S : projectedArea.totalArea;
invAndDynPresArea *= vessel.dynamicPressurekPa;
invAndDynPresArea = 1 / invAndDynPresArea;
visualizationCl = worldLiftArrow.magnitude * invAndDynPresArea;
visualizationCd = worldDragArrow.magnitude * invAndDynPresArea;
}
double fullSatCl = 0, satCl = 0, fullSatCd = 0, satCd = 0;
if (legacyWingModel != null)
{
fullSatCl = aeroVizGUI.FullySaturatedCl;
fullSatCd = aeroVizGUI.FullySaturatedCd;
}
else
{
fullSatCl = aeroVizGUI.FullySaturatedClBody;
fullSatCd = aeroVizGUI.FullySaturatedCdBody;
}
if (aeroVizGUI.TintForCl)
{
satCl = Math.Abs(visualizationCl / fullSatCl);
}
if (aeroVizGUI.TintForCd)
{
satCd = Math.Abs(visualizationCd / fullSatCd);
}
return(new Color((float)satCd, 0.5f * (float)(satCl + satCd), (float)satCl, 0.5f));
}
private void CalculateStallFraction()
{
for (int i = 0; i < _LEGACY_currentWingAeroModel.Count; i++)
{
FARWingAerodynamicModel w = _LEGACY_currentWingAeroModel[i];
vesselInfo.stallFraction += w.GetStall() * w.S;
}
vesselInfo.stallFraction /= wingArea;
}