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, 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;
}
public void ResetClCdCmSteady(Vector3d CoM, InstantConditionSimInput input, out FARCenterQuery center, bool reset_cossweep, bool clear_clcd, bool reset_stall)
{
Vector3d velocity, liftDown, sideways, angVel, velVector;
GetAxisVectors(CoM, input, out velocity, out liftDown, out sideways, out angVel);
velVector = input.fltenv.VelocityVector(velocity);
if (reset_cossweep)
{
for (int i = 0; i < _wingAerodynamicModel.Count; i++)
{
FARWingAerodynamicModel w = _wingAerodynamicModel[i];
if (w == null)
{
continue;
}
w.ResetCosSweepAngle();
}
}
for (int i = 0; i < _wingAerodynamicModel.Count; i++)
{
FARWingAerodynamicModel w = _wingAerodynamicModel[i];
if (!(w && w.part))
{
continue;
}
w.ComputeForceEditor(velVector, input.fltenv);
}
if (clear_clcd)
{
for (int i = 0; i < _wingAerodynamicModel.Count; i++)
{
FARWingAerodynamicModel w = _wingAerodynamicModel[i];
if (!(w && w.part))
{
continue;
}
w.EditorClClear(reset_stall);
}
}
for (int i = 0; i < _wingAerodynamicModel.Count; i++)
{
FARWingAerodynamicModel w = _wingAerodynamicModel[i];
if (!(w && w.part))
{
continue;
}
Vector3d relPos = w.GetAerodynamicCenter() - CoM;
Vector3d vel = velVector + 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(vel, input.fltenv);
}
center = new FARCenterQuery();
for (int i = 0; i < _currentAeroSections.Count; i++)
{
// Rodhern: The hardcoded 2 for density is replaced, but some other parameters are still rough editor approximations.
float reynoldsPerUnitLength = 10000;
float pseudoKnudsenNumber = 0;
double pseudoLengthScale = 1;
float skinFrictionDrag = (float)input.fltenv.SkinFrictionDrag(pseudoLengthScale);
_currentAeroSections[i].PredictionCalculateAeroForces((float)input.fltenv.Rho, (float)input.fltenv.MachNumber,
reynoldsPerUnitLength, pseudoKnudsenNumber, skinFrictionDrag,
velVector, center);
}
}
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;
if (EditorDriver.editorFacility == EditorFacility.VAB)
{
forward = Vector3.up;
up = -Vector3.forward;
}
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;
// Rodhern: The original reference directions (velocity, liftVector, sideways) did not form an orthonormal
// basis. That in turn produced some counterintuitive calculation results, such as coupled yaw and pitch
// derivatives. A more thorough discussion of the topic can be found on the KSP forums:
// https://forum.kerbalspaceprogram.com/index.php?/topic/19321-131-ferram-aerospace-research-v01591-liepmann-4218/&do=findComment&comment=2781270
// The reference directions have been replaced by new ones that are orthonormal by construction.
// In dkavolis branch Vector3.Cross() and Vector3d.Normalize() are used explicitly. There is no apparent
// benefit to this other than possibly improved readability.
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 velocity = forward * cosAlpha * cosBeta;
velocity += right * (sinPhi * sinAlpha * cosBeta + cosPhi * sinBeta);
velocity += -up * (cosPhi * sinAlpha * cosBeta - sinPhi * sinBeta);
velocity.Normalize();
Vector3d liftDown = -forward * sinAlpha;
liftDown += right * sinPhi * cosAlpha;
liftDown += -up * cosPhi * cosAlpha;
liftDown.Normalize();
//Vector3d sideways = -forward * cosAlpha * sinBeta;
//sideways += right * (cosPhi * cosBeta - sinPhi * sinAlpha * sinBeta);
//sideways += up * (cosPhi * sinAlpha * sinBeta + sinPhi * cosBeta);
Vector3d sideways = Vector3.Cross(velocity, liftDown);
sideways.Normalize();
Vector3d angVel = forward * (phiDot - sinAlpha * betaDot);
angVel += right * (cosPhi * alphaDot + cosAlpha * sinPhi * betaDot);
angVel += up * (sinPhi * alphaDot - cosAlpha * cosPhi * betaDot);
for (int i = 0; i < _wingAerodynamicModel.Count; i++)
{
FARWingAerodynamicModel w = _wingAerodynamicModel[i];
if (!(w && w.part))
{
continue;
}
w.ComputeForceEditor(velocity, 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, liftDown);
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, liftDown);
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, 0.005f, velocity.normalized, center);
}
Vector3d centerForce = center.force * 1000;
output.Cl += -Vector3d.Dot(centerForce, liftDown);
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, liftDown);
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.NearlyEqual(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;
}
public void GetClCdCmSteady(InstantConditionSimInput input, out InstantConditionSimOutput output, bool clear, bool reset_stall)
{
Vector3d CoM;
double mass, area, MAC, b; // mass not actually used in these calculations
GetCoMAndSize(out CoM, out mass, out area, out MAC, out b);
FARCenterQuery center;
ResetClCdCmSteady(CoM, input, out center, false, clear, reset_stall);
Vector3d velocity, liftDown, sideways, angVel, velVector;
GetAxisVectors(CoM, input, out velocity, out liftDown, out sideways, out angVel);
velVector = input.fltenv.VelocityVector(velocity);
output = new InstantConditionSimOutput();
for (int i = 0; i < _wingAerodynamicModel.Count; i++)
{
FARWingAerodynamicModel w = _wingAerodynamicModel[i];
if (!(w && w.part) || w.isShielded)
{
continue;
}
Vector3d relPos = w.GetAerodynamicCenter() - CoM;
Vector3d vel = velVector + Vector3d.Cross(angVel, relPos);
Vector3d force = w.ComputeForceEditor(vel, input.fltenv);
output.Cl += -Vector3d.Dot(force, liftDown);
output.Cd += -Vector3d.Dot(force, velocity);
output.Cy += Vector3d.Dot(force, sideways);
Vector3d moment = -Vector3d.Cross(relPos, force);
output.Cm += Vector3d.Dot(moment, sideways);
output.Cn += Vector3d.Dot(moment, liftDown);
output.C_roll += Vector3d.Dot(moment, velocity);
}
Vector3d centerForce = center.force;
output.Cl += -Vector3d.Dot(centerForce, liftDown);
output.Cd += -Vector3d.Dot(centerForce, velocity);
output.Cy += Vector3d.Dot(centerForce, sideways);
Vector3d centerMoment = -center.TorqueAt(CoM);
output.Cm += Vector3d.Dot(centerMoment, sideways);
output.Cn += Vector3d.Dot(centerMoment, liftDown);
output.C_roll += Vector3d.Dot(centerMoment, velocity);
double q = input.fltenv.DynamicPressure();
double recip = 1 / (q * area); // reciprocal value to area and dynamic pressure
output.Cl *= recip;
output.Cd *= recip;
output.Cy *= recip;
output.Cm *= recip / MAC;
output.Cn *= recip / b;
output.C_roll *= recip / b;
}