public void SimulateAeroProperties(out Vector3 aeroForce, out Vector3 aeroTorque, Vector3 velocityWorldVector, double altitude)
{
// Rodhern: It seems that this method, 'SimulateAeroProperties', is only used in FARAPI, which in turn can be used by say KSPTrajectories.
// The parameter 'FARCenterQuery dummy' is from a code fix by Benjamin Chung (commit 18fbb9d29431679a4de9dfc22a443f400d2d4f8b).
FARCenterQuery center = new FARCenterQuery();
FARCenterQuery dummy = new FARCenterQuery();
float pressure;
float density;
float temperature;
float speedOfSound;
CelestialBody body = vessel.mainBody; //Calculate main gas properties
pressure = (float)body.GetPressure(altitude);
temperature = (float)body.GetTemperature(altitude);
density = (float)body.GetDensity(pressure, temperature);
speedOfSound = (float)body.GetSpeedOfSound(pressure, density);
if (pressure <= 0 || temperature <= 0 || density <= 0 || speedOfSound <= 0)
{
aeroForce = Vector3.zero;
aeroTorque = Vector3.zero;
return;
}
float velocityMag = velocityWorldVector.magnitude;
float machNumber = velocityMag / speedOfSound;
float reynoldsNumber = (float)FARAeroUtil.CalculateReynoldsNumber(density, Length, velocityMag, machNumber, temperature, body.atmosphereAdiabaticIndex);
float reynoldsPerLength = reynoldsNumber / (float)Length;
float pseudoKnudsenNumber = machNumber / (reynoldsNumber + machNumber);
float skinFriction = (float)FARAeroUtil.SkinFrictionDrag(reynoldsNumber, machNumber);
FlightEnv fenv = FlightEnv.NewPredicted(vessel.mainBody, altitude, machNumber);
if (_currentAeroSections != null)
{
for (int i = 0; i < _currentAeroSections.Count; i++)
{
FARAeroSection curSection = _currentAeroSections[i];
if (curSection != null)
{
curSection.PredictionCalculateAeroForces(density, machNumber, reynoldsPerLength, pseudoKnudsenNumber, skinFriction, velocityWorldVector, center);
}
}
for (int i = 0; i < _legacyWingModels.Count; i++)
{
FARWingAerodynamicModel curWing = _legacyWingModels[i];
if ((object)curWing != null)
{
Vector3d force = curWing.PrecomputeCenterOfLift(velocityWorldVector, fenv, dummy);
center.AddForce(curWing.transform.position, force);
}
}
}
aeroForce = center.force;
aeroTorque = center.TorqueAt(vessel.CoM);
}
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);
}
}
public void SimulateAeroProperties(
out Vector3 aeroForce,
out Vector3 aeroTorque,
Vector3 velocityWorldVector,
double altitude
)
{
Vector3d position = vessel.CurrentPosition(altitude);
if (velocityWorldVector.NearlyEqual(lastSimResults.VelocityVector) &&
(FARAtmosphere.IsCustom
// Custom atmospheres are not guaranteed to be independent of latitude and longitude
? position.NearlyEqual(lastSimResults.Position)
: altitude.NearlyEqual(lastSimResults.Position.z)))
{
aeroForce = lastSimResults.Force;
aeroTorque = lastSimResults.Torque;
return;
}
var center = new FARCenterQuery();
var dummy = new FARCenterQuery();
//Calculate main gas properties
GasProperties properties = FARAtmosphere.GetGasProperties(vessel.mainBody, position, Planetarium.GetUniversalTime());
if (properties.Pressure <= 0 || properties.Temperature <= 0)
{
aeroForce = Vector3.zero;
aeroTorque = Vector3.zero;
return;
}
float velocityMag = velocityWorldVector.magnitude;
float machNumber = (float)(velocityMag / properties.SpeedOfSound);
float reynoldsNumber = (float)FARAeroUtil.CalculateReynoldsNumber(properties.Density,
Length,
velocityMag,
machNumber,
properties.Temperature,
properties.AdiabaticIndex);
float reynoldsPerLength = reynoldsNumber / (float)Length;
float skinFriction = (float)FARAeroUtil.SkinFrictionDrag(reynoldsNumber, machNumber);
float pseudoKnudsenNumber = machNumber / (reynoldsNumber + machNumber);
if (_currentAeroSections != null)
{
foreach (FARAeroSection curSection in _currentAeroSections)
{
curSection?.PredictionCalculateAeroForces((float)properties.Density,
machNumber,
reynoldsPerLength,
pseudoKnudsenNumber,
skinFriction,
velocityWorldVector,
center);
}
foreach (FARWingAerodynamicModel curWing in _legacyWingModels)
{
if (curWing != null)
{
center.AddForce(curWing.transform.position,
curWing.PrecomputeCenterOfLift(velocityWorldVector,
machNumber,
properties.Density,
dummy));
}
}
}
aeroForce = center.force;
aeroTorque = center.TorqueAt(vessel.CoM);
lastSimResults = new CachedSimResults(velocityWorldVector, position, aeroForce, aeroTorque);
}
public void SimulateAeroProperties(
out Vector3 aeroForce,
out Vector3 aeroTorque,
Vector3 velocityWorldVector,
double altitude
)
{
var center = new FARCenterQuery();
var dummy = new FARCenterQuery();
CelestialBody body = vessel.mainBody; //Calculate main gas properties
float pressure = (float)body.GetPressure(altitude);
float temperature = (float)body.GetTemperature(altitude);
float density = (float)body.GetDensity(pressure, temperature);
float speedOfSound = (float)body.GetSpeedOfSound(pressure, density);
if (pressure <= 0 || temperature <= 0 || density <= 0 || speedOfSound <= 0)
{
aeroForce = Vector3.zero;
aeroTorque = Vector3.zero;
return;
}
float velocityMag = velocityWorldVector.magnitude;
float machNumber = velocityMag / speedOfSound;
float reynoldsNumber =
(float)FARAeroUtil.CalculateReynoldsNumber(density,
Length,
velocityMag,
machNumber,
temperature,
body.atmosphereAdiabaticIndex);
float reynoldsPerLength = reynoldsNumber / (float)Length;
float skinFriction = (float)FARAeroUtil.SkinFrictionDrag(reynoldsNumber, machNumber);
float pseudoKnudsenNumber = machNumber / (reynoldsNumber + machNumber);
if (_currentAeroSections != null)
{
foreach (FARAeroSection curSection in _currentAeroSections)
{
curSection?.PredictionCalculateAeroForces(density,
machNumber,
reynoldsPerLength,
pseudoKnudsenNumber,
skinFriction,
velocityWorldVector,
center);
}
foreach (FARWingAerodynamicModel curWing in _legacyWingModels)
{
if (!(curWing is null))
{
center.AddForce(curWing.transform.position,
curWing.PrecomputeCenterOfLift(velocityWorldVector,
machNumber,
density,
dummy));
}
}
}
aeroForce = center.force;
aeroTorque = center.TorqueAt(vessel.CoM);
}
public void SimulateAeroProperties(
out Vector3 aeroForce,
out Vector3 aeroTorque,
Vector3 velocityWorldVector,
double altitude
)
{
var center = new FARCenterQuery();
var dummy = new FARCenterQuery();
//Calculate main gas properties
GasProperties properties = FARAtmosphere.GetGasProperties(vessel, altitude, Planetarium.GetUniversalTime());
if (properties.Pressure <= 0 || properties.Temperature <= 0)
{
aeroForce = Vector3.zero;
aeroTorque = Vector3.zero;
return;
}
float velocityMag = velocityWorldVector.magnitude;
float machNumber = (float)(velocityMag / properties.SpeedOfSound);
float reynoldsNumber = (float)FARAeroUtil.CalculateReynoldsNumber(properties.Density,
Length,
velocityMag,
machNumber,
properties.Temperature,
properties.AdiabaticIndex);
float reynoldsPerLength = reynoldsNumber / (float)Length;
float skinFriction = (float)FARAeroUtil.SkinFrictionDrag(reynoldsNumber, machNumber);
float pseudoKnudsenNumber = machNumber / (reynoldsNumber + machNumber);
if (_currentAeroSections != null)
{
foreach (FARAeroSection curSection in _currentAeroSections)
{
curSection?.PredictionCalculateAeroForces((float)properties.Density,
machNumber,
reynoldsPerLength,
pseudoKnudsenNumber,
skinFriction,
velocityWorldVector,
center);
}
foreach (FARWingAerodynamicModel curWing in _legacyWingModels)
{
if (curWing != null)
{
center.AddForce(curWing.transform.position,
curWing.PrecomputeCenterOfLift(velocityWorldVector,
machNumber,
properties.Density,
dummy));
}
}
}
aeroForce = center.force;
aeroTorque = center.TorqueAt(vessel.CoM);
}
