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;
}
}