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 SimulateAeroProperties(out Vector3 aeroForce, out Vector3 aeroTorque, Vector3 velocityWorldVector, double altitude)
{
FARCenterQuery center = 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 skinFriction = (float)FARAeroUtil.SkinFrictionDrag(reynoldsNumber, machNumber);
float pseudoKnudsenNumber = machNumber / (reynoldsNumber + 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)
{
curWing.PrecomputeCenterOfLift(velocityWorldVector, machNumber, density, center);
}
}
}
aeroForce = center.force;
aeroTorque = center.TorqueAt(vessel.CoM);
}
private void CalculateAndApplyVesselAeroProperties()
{
float atmDensity = (float)vessel.atmDensity;
if (atmDensity <= 0)
{
MachNumber = 0;
ReynoldsNumber = 0;
return;
}
MachNumber = vessel.mach;
ReynoldsNumber = FARAeroUtil.CalculateReynoldsNumber(vessel.atmDensity,
Length,
vessel.srfSpeed,
MachNumber,
FlightGlobals.getExternalTemperature((float)vessel
.altitude,
vessel.mainBody),
vessel.mainBody.atmosphereAdiabaticIndex);
float skinFrictionDragCoefficient = (float)FARAeroUtil.SkinFrictionDrag(ReynoldsNumber, MachNumber);
float pseudoKnudsenNumber = (float)(MachNumber / (ReynoldsNumber + MachNumber));
Vector3 frameVel = Krakensbane.GetFrameVelocityV3f();
//start from the top and come down to improve performance if it needs to remove anything
for (int i = _currentAeroModules.Count - 1; i >= 0; i--)
{
FARAeroPartModule m = _currentAeroModules[i];
if (m != null && m.part != null && m.part.partTransform != null)
{
m.UpdateVelocityAndAngVelocity(frameVel);
}
else
{
_currentAeroModules.RemoveAt(i);
}
}
foreach (FARAeroSection aeroSection in _currentAeroSections)
{
aeroSection.FlightCalculateAeroForces((float)MachNumber,
(float)(ReynoldsNumber / Length),
pseudoKnudsenNumber,
skinFrictionDragCoefficient);
}
_vesselIntakeRamDrag.ApplyIntakeRamDrag((float)MachNumber, vessel.srf_velocity.normalized);
foreach (FARAeroPartModule m in _currentAeroModules)
{
m.ApplyForces();
}
}
private void CalculateAndApplyVesselAeroProperties()
{
float atmDensity = (float)_vessel.atmDensity;
if (atmDensity <= 0)
{
machNumber = 0;
reynoldsNumber = 0;
return;
}
machNumber = _vessel.mach;
reynoldsNumber = FARAeroUtil.CalculateReynoldsNumber(_vessel.atmDensity, Length, _vessel.srfSpeed, machNumber, FlightGlobals.getExternalTemperature((float)_vessel.altitude, _vessel.mainBody), _vessel.mainBody.atmosphereAdiabaticIndex);
float skinFrictionDragCoefficient = (float)FARAeroUtil.SkinFrictionDrag(reynoldsNumber, machNumber);
Vector3 frameVel = Krakensbane.GetFrameVelocityV3f();
if (_updateQueued) //only happens if we have an voxelization scheduled, then we need to check for null
{
for (int i = _currentAeroModules.Count - 1; i >= 0; i--) //start from the top and come down to improve performance if it needs to remove anything
{
FARAeroPartModule m = _currentAeroModules[i];
if (m != null)
{
m.UpdateVelocityAndAngVelocity(frameVel);
}
else
{
_currentAeroModules.RemoveAt(i);
i++;
}
}
}
else //otherwise, we don't need to do Unity's expensive "is this part dead" null-check
{
for (int i = _currentAeroModules.Count - 1; i >= 0; i--) //start from the top and come down to improve performance if it needs to remove anything
{
FARAeroPartModule m = _currentAeroModules[i];
m.UpdateVelocityAndAngVelocity(frameVel);
}
}
for (int i = 0; i < _currentAeroSections.Count; i++)
{
_currentAeroSections[i].FlightCalculateAeroForces(atmDensity, (float)machNumber, (float)(reynoldsNumber / Length), skinFrictionDragCoefficient);
}
_vesselIntakeRamDrag.ApplyIntakeRamDrag((float)machNumber, _vessel.srf_velocity.normalized, (float)_vessel.dynamicPressurekPa);
for (int i = 0; i < _currentAeroModules.Count; i++)
{
FARAeroPartModule m = _currentAeroModules[i];
m.ApplyForces();
}
}
private void CalculateAndApplyVesselAeroProperties()
{
float atmDensity = (float)_vessel.atmDensity;
if (atmDensity <= 0)
{
machNumber = 0;
reynoldsNumber = 0;
return;
}
machNumber = _vessel.mach;
reynoldsNumber = FARAeroUtil.CalculateReynoldsNumber(_vessel.atmDensity, Length, _vessel.srfSpeed, machNumber, FlightGlobals.getExternalTemperature((float)_vessel.altitude, _vessel.mainBody), _vessel.mainBody.atmosphereAdiabaticIndex);
float skinFrictionDragCoefficient = (float)FARAeroUtil.SkinFrictionDrag(reynoldsNumber, machNumber);
Vector3 frameVel = Krakensbane.GetFrameVelocityV3f();
for (int i = 0; i < _currentAeroModules.Count; i++)
{
FARAeroPartModule m = _currentAeroModules[i];
if (m != null)
{
m.UpdateVelocityAndAngVelocity(frameVel);
}
else
{
_currentAeroModules.RemoveAt(i);
i--;
}
}
for (int i = 0; i < _currentAeroSections.Count; i++)
{
_currentAeroSections[i].FlightCalculateAeroForces(atmDensity, (float)machNumber, (float)(reynoldsNumber / Length), skinFrictionDragCoefficient);
}
_vesselIntakeRamDrag.ApplyIntakeRamDrag((float)machNumber, _vessel.srf_velocity.normalized, (float)_vessel.dynamicPressurekPa);
for (int i = 0; i < _currentAeroModules.Count; i++)
{
FARAeroPartModule m = _currentAeroModules[i];
if ((object)m != null)
{
m.ApplyForces();
}
}
}
public void SimulateAeroProperties(out Vector3 aeroForce, out Vector3 aeroTorque, Vector3 velocityWorldVector, double altitude)
{
FARCenterQuery center = 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);
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 pseudoLanchesterNumber = machNumber / (reynoldsNumber + machNumber);
for (int i = 0; i < _currentAeroSections.Count; i++)
{
_currentAeroSections[i].PredictionCalculateAeroForces(density, machNumber, reynoldsPerLength, pseudoLanchesterNumber, skinFriction, velocityWorldVector, center);
}
for (int i = 0; i < _legacyWingModels.Count; i++)
{
_legacyWingModels[i].PrecomputeCenterOfLift(velocityWorldVector, machNumber, density, center);
}
aeroForce = center.force;
aeroTorque = center.TorqueAt(_vessel.CoM);
}
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();
//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);
}
