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);
for(int i = 0; i < _currentAeroSections.Count; i++)
_currentAeroSections[i].PredictionCalculateAeroForces(density, machNumber, reynoldsPerLength, 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);
}
void UpdateAerodynamicCenter()
{
FARCenterQuery aeroSection, dummy;
aeroSection = new FARCenterQuery();
dummy = new FARCenterQuery();
if((object)EditorLogic.RootPart == null)
return;
Vector3 vel_base, vel_fuzz;
Transform rootPartTrans = EditorLogic.RootPart.partTransform;
if (EditorDriver.editorFacility == EditorFacility.SPH)
{
vel_base = Vector3.forward;
vel_fuzz = 0.02f * Vector3.up;
}
else
{
vel_base = Vector3.up;
vel_fuzz = -0.02f * Vector3.forward;
}
Vector3 vel = (vel_base - vel_fuzz).normalized;
for(int i = 0; i < _currentAeroSections.Count; i++)
{
FARAeroSection section = _currentAeroSections[i];
section.PredictionCalculateAeroForces(1, 0.5f, 100000, 0.005f, vel, aeroSection);
}
FARBaseAerodynamics.PrecomputeGlobalCenterOfLift(aeroSection, dummy, vel, 1);
Vector3 pos = Vector3.zero;//rootPartTrans.position;
float mass = 0;
for(int i = 0; i < EditorLogic.SortedShipList.Count; i++)
{
Part p = EditorLogic.SortedShipList[i];
float tmpMass = p.mass + p.GetResourceMass();
mass += tmpMass;
pos += p.partTransform.position * tmpMass;
}
pos /= mass;
Vector3 avgForcePos = Vector3.zero;
Vector3 force0, moment0;
force0 = aeroSection.force;
moment0 = aeroSection.TorqueAt(pos);
avgForcePos += aeroSection.GetPos();
//aeroSection.force = -aeroSection.force;
//aeroSection.torque = -aeroSection.torque;
aeroSection.ClearAll();
vel = (vel_base + vel_fuzz).normalized;
for (int i = 0; i < _currentAeroSections.Count; i++)
{
FARAeroSection section = _currentAeroSections[i];
section.PredictionCalculateAeroForces(1, 0.5f, 100000, 0.005f, vel, aeroSection);
}
FARBaseAerodynamics.PrecomputeGlobalCenterOfLift(aeroSection, dummy, vel, 1);
Vector3 force1, moment1;
force1 = aeroSection.force;
moment1 = aeroSection.TorqueAt(pos);
avgForcePos += aeroSection.GetPos();
aeroSection.ClearAll();
avgForcePos *= 0.5f;
Vector3 deltaForce = force1 - force0;
Vector3 deltaMoment = moment1 - moment0;
Vector3 deltaForcePerp = Vector3.ProjectOnPlane(deltaForce, vel_base);
float deltaForcePerpMag = deltaForcePerp.magnitude;
Vector3 deltaForcePerpNorm = deltaForcePerp / deltaForcePerpMag;
Vector3 deltaMomentPerp = deltaMoment - Vector3.Dot(deltaMoment, deltaForcePerpNorm) * deltaForcePerpNorm - Vector3.Project(deltaMoment, vel_base);
//float dist = deltaMomentPerp.magnitude / deltaForcePerpMag;
//vesselRootLocalAeroCenter = vel_base * dist;
vesselRootLocalAeroCenter = deltaMomentPerp.magnitude / deltaForcePerpMag * vel_base * Math.Sign(Vector3.Dot(Vector3.Cross(deltaForce, deltaMoment), vel_base));
//Debug.Log(dist + " " + deltaMomentPerp.magnitude + " " + deltaForcePerpMag);
//vesselRootLocalAeroCenter += avgForcePos;
//avgForcePos = rootPartTrans.worldToLocalMatrix.MultiplyPoint3x4(avgForcePos);
//vesselRootLocalAeroCenter += Vector3.ProjectOnPlane(avgForcePos, Vector3.up);
//vesselRootLocalAeroCenter = aeroSection.GetPos();
vesselRootLocalAeroCenter += pos;//Vector3.ProjectOnPlane(avgForcePos - pos, vesselRootLocalAeroCenter) + pos;
vesselRootLocalAeroCenter = rootPartTrans.worldToLocalMatrix.MultiplyPoint3x4(vesselRootLocalAeroCenter);
}
public void GetClCdCmSteady(InstantConditionSimInput input, out InstantConditionSimOutput output, bool clear, bool reset_stall = false)
{
output = new InstantConditionSimOutput();
double area = 0;
double MAC = 0;
double b_2 = 0;
Vector3d forward = Vector3.forward;
Vector3d up = Vector3.up;
Vector3d right = Vector3.right;
Vector3d CoM = Vector3d.zero;
double mass = 0;
List<Part> partsList = EditorLogic.SortedShipList;
for (int i = 0; i < partsList.Count; i++)
{
Part p = partsList[i];
if (FARAeroUtil.IsNonphysical(p))
continue;
double partMass = p.mass;
if (p.Resources.Count > 0)
partMass += p.GetResourceMass();
//partMass += p.GetModuleMass(p.mass);
// If you want to use GetModuleMass, you need to start from p.partInfo.mass, not p.mass
CoM += partMass * (Vector3d)p.transform.TransformPoint(p.CoMOffset);
mass += partMass;
}
CoM /= mass;
if (EditorDriver.editorFacility == EditorFacility.VAB)
{
forward = Vector3.up;
up = -Vector3.forward;
}
double sinAlpha = Math.Sin(input.alpha * Math.PI / 180);
double cosAlpha = Math.Sqrt(Math.Max(1 - sinAlpha * sinAlpha, 0));
double sinBeta = Math.Sin(input.beta * Math.PI / 180);
double cosBeta = Math.Sqrt(Math.Max(1 - sinBeta * sinBeta, 0));
double sinPhi = Math.Sin(input.phi * Math.PI / 180);
double cosPhi = Math.Sqrt(Math.Max(1 - sinPhi * sinPhi, 0));
double alphaDot = input.alphaDot * Math.PI / 180;
double betaDot = input.betaDot * Math.PI / 180;
double phiDot = input.phiDot * Math.PI / 180;
Vector3d AngVel = (phiDot - sinAlpha * betaDot) * forward;
AngVel += (cosPhi * alphaDot + cosAlpha * sinPhi * betaDot) * right;
AngVel += (sinPhi * alphaDot - cosAlpha * cosPhi * betaDot) * up;
Vector3d velocity = forward * cosAlpha * cosBeta;
velocity += right * (sinPhi * cosAlpha * cosBeta + cosPhi * sinBeta);
velocity += -up * cosPhi * (sinAlpha * cosBeta + sinBeta);
velocity.Normalize();
//this is negative wrt the ground
Vector3d liftVector = -forward * sinAlpha + right * sinPhi * cosAlpha - up * cosPhi * cosAlpha;
Vector3d sideways = Vector3.Cross(velocity, liftVector).normalized;
for (int i = 0; i < _wingAerodynamicModel.Count; i++)
{
FARWingAerodynamicModel w = _wingAerodynamicModel[i];
if (!(w && w.part))
continue;
w.ComputeForceEditor(velocity.normalized, input.machNumber, 2);
if (clear)
w.EditorClClear(reset_stall);
Vector3d relPos = w.GetAerodynamicCenter() - CoM;
Vector3d vel = velocity + Vector3d.Cross(AngVel, relPos);
if (w is FARControllableSurface)
(w as FARControllableSurface).SetControlStateEditor(CoM, vel, (float)input.pitchValue, 0, 0, input.flaps, input.spoilers);
else if (w.isShielded)
continue;
//w.ComputeForceEditor(velocity, input.machNumber); //do this just to get the AC right
Vector3d force = w.ComputeForceEditor(vel.normalized, input.machNumber, 2) * 1000;
output.Cl += -Vector3d.Dot(force, liftVector);
output.Cy += Vector3d.Dot(force, sideways);
output.Cd += -Vector3d.Dot(force, velocity);
Vector3d moment = -Vector3d.Cross(relPos, force);
output.Cm += Vector3d.Dot(moment, sideways);
output.Cn += Vector3d.Dot(moment, liftVector);
output.C_roll += Vector3d.Dot(moment, velocity);
//w.ComputeClCdEditor(vel.normalized, input.machNumber);
/*double tmpCl = w.GetCl() * w.S;
output.Cl += tmpCl * -Vector3d.Dot(w.GetLiftDirection(), liftVector);
output.Cy += tmpCl * -Vector3d.Dot(w.GetLiftDirection(), sideways);
double tmpCd = w.GetCd() * w.S;
output.Cd += tmpCd;
output.Cm += tmpCl * Vector3d.Dot((relPos), velocity) * -Vector3d.Dot(w.GetLiftDirection(), liftVector) + tmpCd * -Vector3d.Dot((relPos), liftVector);
output.Cn += tmpCd * Vector3d.Dot((relPos), sideways) + tmpCl * Vector3d.Dot((relPos), velocity) * -Vector3d.Dot(w.GetLiftDirection(), sideways);
output.C_roll += tmpCl * Vector3d.Dot((relPos), sideways) * -Vector3d.Dot(w.GetLiftDirection(), liftVector);*/
area += w.S;
MAC += w.GetMAC() * w.S;
b_2 += w.Getb_2() * w.S;
}
FARCenterQuery center = new FARCenterQuery();
for (int i = 0; i < _currentAeroSections.Count; i++)
{
_currentAeroSections[i].PredictionCalculateAeroForces(2, (float)input.machNumber, 10000, 0.005f, velocity.normalized, center);
}
Vector3d centerForce = center.force * 1000;
output.Cl += -Vector3d.Dot(centerForce, liftVector);
output.Cy += Vector3d.Dot(centerForce, sideways);
output.Cd += -Vector3d.Dot(centerForce, velocity);
Vector3d centerMoment = -center.TorqueAt(CoM) * 1000;
output.Cm += Vector3d.Dot(centerMoment, sideways);
output.Cn += Vector3d.Dot(centerMoment, liftVector);
output.C_roll += Vector3d.Dot(centerMoment, velocity);
/*for (int i = 0; i < FARAeroUtil.CurEditorParts.Count; i++)
{
Part p = FARAeroUtil.CurEditorParts[i];
if (FARAeroUtil.IsNonphysical(p))
continue;
Vector3 part_pos = p.transform.TransformPoint(p.CoMOffset) - CoM;
double partMass = p.mass;
if (p.Resources.Count > 0)
partMass += p.GetResourceMass();
double stock_drag = partMass * p.maximum_drag * FlightGlobals.DragMultiplier * 1000;
output.Cd += stock_drag;
output.Cm += stock_drag * -Vector3d.Dot(part_pos, liftVector);
output.Cn += stock_drag * Vector3d.Dot(part_pos, sideways);
}*/
if (area == 0)
{
area = _maxCrossSectionFromBody;
b_2 = 1;
MAC = _bodyLength;
}
double recipArea = 1 / area;
MAC *= recipArea;
b_2 *= recipArea;
output.Cl *= recipArea;
output.Cd *= recipArea;
output.Cm *= recipArea / MAC;
output.Cy *= recipArea;
output.Cn *= recipArea / b_2;
output.C_roll *= recipArea / b_2;
}
