public void ApplyForce(FARAeroSection.PartData pd, Vector3 localVel, Vector3 forceVector, Vector3 torqueVector)
{
double tmp = 0.0005 * Vector3.SqrMagnitude(localVel);
double dynamicPressurekPa = tmp * atmDensity;
double dragFactor = dynamicPressurekPa *
Mathf.Max(PhysicsGlobals.DragCurvePseudoReynolds.Evaluate(atmDensity *
Vector3.Magnitude(localVel)),
1.0f);
double liftFactor = dynamicPressurekPa;
Vector3 localVelNorm = Vector3.Normalize(localVel);
Vector3 localForceTemp = Vector3.Dot(localVelNorm, forceVector) * localVelNorm;
Vector3 partLocalForce =
localForceTemp * (float)dragFactor + (forceVector - localForceTemp) * (float)liftFactor;
forceVector = pd.aeroModule.part.transform.TransformDirection(partLocalForce);
torqueVector = pd.aeroModule.part.transform.TransformDirection(torqueVector * (float)dynamicPressurekPa);
if (float.IsNaN(forceVector.x) || float.IsNaN(torqueVector.x))
{
return;
}
Vector3 centroid =
pd.aeroModule.part.transform.TransformPoint(pd.centroidPartSpace - pd.aeroModule.part.CoMOffset);
center.AddForce(centroid, forceVector);
center.AddTorque(torqueVector);
}
private void CalculateTotalAeroForce()
{
aeroForces.ClearAll();
if (_vessel.dynamicPressurekPa <= 0.00001)
{
return;
}
if (_currentAeroModules != null)
{
for (int i = 0; i < _currentAeroModules.Count; i++)
{
FARAeroPartModule m = _currentAeroModules[i];
if ((object)m != null)
{
aeroForces.AddForce(m.transform.position, m.totalWorldSpaceAeroForce);
aeroForces.AddTorque(m.worldSpaceTorque);
}
}
}
/*
* for (int i = 0; i < _LEGACY_currentWingAeroModel.Count; i++)
* {
* FARWingAerodynamicModel w = _LEGACY_currentWingAeroModel[i];
* if ((object)w == null)
* continue;
* totalAeroForceVector += w.worldSpaceForce;
* aeroForces.AddForce(w.AerodynamicCenter, w.worldSpaceForce);
*
* totalAeroForceVector += w.worldSpaceForce;
* totalAeroTorqueVector += Vector3.Cross(w.AerodynamicCenter - _vessel.CoM, w.worldSpaceForce);
* }
*
* for(int i = 0; i < _vessel.parts.Count; i++)
* {
* Part p = _vessel.parts[i];
* totalAeroForceVector += -p.dragVectorDir * p.dragScalar; // dragVectorDir is actually the velocity vector direction
* }
*/
}
private void CalculateTotalAeroForce()
{
aeroForces.ClearAll();
if (_vessel.dynamicPressurekPa <= 0.00001)
{
return;
}
if (_currentAeroModules == null)
{
return;
}
foreach (FARAeroPartModule m in _currentAeroModules)
{
if (m is null)
{
continue;
}
aeroForces.AddForce(m.transform.position, m.totalWorldSpaceAeroForce);
aeroForces.AddTorque(m.worldSpaceTorque);
}
}
