public static void PrecomputeGlobalCenterOfLift(FARCenterQuery lift, FARCenterQuery dummy, Vector3 vel)
{
/* Center of lift is the location where the derivative of
* the total torque provided by aerodynamic forces relative to
* AoA is zero (or at least minimal). This approximates the
* derivative by a simple subtraction, like before. */
var parts = GetAllEditorModules();
for (int i = 0; i < parts.Count; i++)
{
FARBaseAerodynamics ba = parts[i];
ba.velocityEditor = vel;
ba.ResetCenterOfLift();
}
FlightEnv defaultfltenv = FlightEnv.NewDefaultVal();
// run computations twice to let things like flap interactions settle
for (int i = 0; i < parts.Count; i++)
{
FARBaseAerodynamics ba = parts[i];
ba.PrecomputeCenterOfLift(vel, defaultfltenv, dummy);
}
for (int i = 0; i < parts.Count; i++)
{
FARBaseAerodynamics ba = parts[i];
ba.PrecomputeCenterOfLift(vel, defaultfltenv, lift);
}
}
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 InstantConditionSimVars(InstantConditionSim parent, CelestialBody body, double altitude, double machNumber, double neededCl, double beta, double phi, int flap, bool spoilers)
{
this.parent = parent;
this.neededCl = neededCl;
this.CoM = parent.GetCoM();
FlightEnv fltenv = FlightEnv.NewSim(body, altitude, machNumber);
iterationInput = new InstantConditionSimInput(0, beta, phi, 0, 0, 0, fltenv, 0, flap, spoilers);
iterationOutput = new InstantConditionSimOutput();
}
public InstantConditionSimInput(double alpha, double beta, double phi, double alphaDot, double betaDot, double phiDot, FlightEnv fltenv, double pitchValue, int flaps, bool spoilers)
{
this.alpha = alpha;
this.beta = beta;
this.phi = phi;
this.alphaDot = alphaDot;
this.betaDot = betaDot;
this.phiDot = phiDot;
this.fltenv = fltenv;
this.pitchValue = pitchValue;
this.flaps = flaps;
this.spoilers = spoilers;
}
/// <summary>
/// The single parameter constructor creates an object that represents
/// an artificial default condition. This default condition is straight
/// and level flight, flaps and spoilers retracted, yoke centered, at
/// mach 0.5 in a 1-density (kg/m3) atmosphere (in Kerbin's case).
/// At Kerbin that is roughly travelling at altitude 1 km at 170 m/s.
/// </summary>
public InstantConditionSimInput(CelestialBody body)
{
this.fltenv = FlightEnv.NewDefaultVal(body);
}
public virtual Vector3d PrecomputeCenterOfLift(Vector3d velocity, FlightEnv fltenv, FARCenterQuery center)
{
return(Vector3d.zero);
}
public GraphData MachNumberSweep(double aoAdegrees, double pitch, double lowerBound, double upperBound, int numPoints, int flapSetting, bool spoilers, CelestialBody body)
{
FARAeroUtil.UpdateCurrentActiveBody(body);
FARAeroUtil.ResetEditorParts();
double[] ClValues = new double[(int)numPoints];
double[] CdValues = new double[(int)numPoints];
double[] CmValues = new double[(int)numPoints];
double[] LDValues = new double[(int)numPoints];
double[] AlphaValues = new double[(int)numPoints];
InstantConditionSimInput input = new InstantConditionSimInput(aoAdegrees, 0, 0, 0, 0, 0, FlightEnv.NewDefaultVal(body), pitch, flapSetting, spoilers);
for (int i = 0; i < numPoints; i++)
{
input.fltenv.MachNumber = lowerBound + (upperBound - lowerBound) * (i == 0? 0 : i / (numPoints - 1.0));
if (input.fltenv.MachNumber < 1E-3)
{
input.fltenv.MachNumber = 1E-3;
}
InstantConditionSimOutput output;
_instantCondition.GetClCdCmSteady(input, out output, i == 0, false);
AlphaValues[i] = input.fltenv.MachNumber;
ClValues[i] = output.Cl;
CdValues[i] = output.Cd;
CmValues[i] = output.Cm;
LDValues[i] = output.Cl * 0.1 / output.Cd;
}
GraphData data = new GraphData();
data.xValues = AlphaValues;
data.AddData(ClValues, GUIColors.GetColor(0), Localizer.Format("FARAbbrevCl"), true);
data.AddData(CdValues, GUIColors.GetColor(1), Localizer.Format("FARAbbrevCd"), true);
data.AddData(CmValues, GUIColors.GetColor(2), Localizer.Format("FARAbbrevCm"), true);
data.AddData(LDValues, GUIColors.GetColor(3), Localizer.Format("FARAbbrevL_D"), true);
data.exportdata.AddSizeVariables(_instantCondition, pitch, flapSetting, spoilers);
data.exportdata.AddMachSweepXVariable(aoAdegrees, AlphaValues);
data.exportdata.AddYVariables(data);
return(data);
}
public int ExportSweep(CelestialBody body, double pitch, int flapSetting, bool spoilers)
{
if (!IsReady())
{
return(0);
}
FARAeroUtil.UpdateCurrentActiveBody(body);
FARAeroUtil.ResetEditorParts();
StaticAnalysisExportFile exportdata = new StaticAnalysisExportFile();
InstantConditionSimInput input = new InstantConditionSimInput(0, 0, 0, 0, 0, 0, FlightEnv.NewDefaultVal(body), pitch, flapSetting, spoilers);
InstantConditionSimOutput output;
Vector3d centerofmass = _instantCondition.GetCoM();
// Loop through each combination (two dimensions).
foreach (float mach in exportdata.MachNumberList)
{
input.fltenv.MachNumber = mach;
input.alpha = 0; // zero is used as a neutral value for the reset
_instantCondition.ResetClCdCmSteady(centerofmass, input); // reset old results (particularly cossweep) that may not reflect the current mach number
foreach (float aoadeg in exportdata.AoADegreeList)
{
input.alpha = aoadeg;
_instantCondition.GetClCdCmSteady(input, out output, true, true);
exportdata.AddDatapoint(mach, aoadeg, output.Cl, output.Cd, output.Cm);
}
}
exportdata.Export();
return(exportdata.DataCount);
}
public GraphData AngleOfAttackSweep(double machNumber, double pitch, double lowerBound, double upperBound, int numPoints, int flapSetting, bool spoilers, CelestialBody body)
{
if (machNumber < 1E-3)
{
machNumber = 1E-3;
}
FARAeroUtil.UpdateCurrentActiveBody(body);
FARAeroUtil.ResetEditorParts();
double[] ClValues = new double[(int)numPoints];
double[] CdValues = new double[(int)numPoints];
double[] CmValues = new double[(int)numPoints];
double[] LDValues = new double[(int)numPoints];
double[] AlphaValues = new double[(int)numPoints];
double[] ClValues2 = new double[(int)numPoints];
double[] CdValues2 = new double[(int)numPoints];
double[] CmValues2 = new double[(int)numPoints];
double[] LDValues2 = new double[(int)numPoints];
InstantConditionSimInput input = new InstantConditionSimInput(0, 0, 0, 0, 0, 0, FlightEnv.NewDefaultVal(body), pitch, flapSetting, spoilers);
input.fltenv.MachNumber = machNumber;
for (int i = 0; i < 2 * numPoints; i++)
{
double angle = 0;
if (i < numPoints)
{
angle = lowerBound + (upperBound - lowerBound) * (i == 0? 0 : i / (numPoints - 1.0));
}
else
{
angle = upperBound + (lowerBound - upperBound) * (i == numPoints ? 0 : (i - numPoints) / (numPoints - 1.0));
}
input.alpha = angle;
InstantConditionSimOutput output;
_instantCondition.GetClCdCmSteady(input, out output, i == 0, false);
if (i < numPoints)
{
AlphaValues[i] = angle;
ClValues[i] = output.Cl;
CdValues[i] = output.Cd;
CmValues[i] = output.Cm;
LDValues[i] = output.Cl * 0.1 / output.Cd;
}
else
{
ClValues2[numPoints * 2 - 1 - i] = output.Cl;
CdValues2[numPoints * 2 - 1 - i] = output.Cd;
CmValues2[numPoints * 2 - 1 - i] = output.Cm;
LDValues2[numPoints * 2 - 1 - i] = output.Cl * 0.1 / output.Cd;
}
}
GraphData data = new GraphData();
data.xValues = AlphaValues;
data.AddData(ClValues2, GUIColors.GetColor(0) * 0.5f, "Cl2", false);
data.AddData(ClValues, GUIColors.GetColor(0), Localizer.Format("FARAbbrevCl"), true);
data.AddData(CdValues2, GUIColors.GetColor(1) * 0.5f, "Cd2", false);
data.AddData(CdValues, GUIColors.GetColor(1), Localizer.Format("FARAbbrevCd"), true);
data.AddData(CmValues2, GUIColors.GetColor(2) * 0.5f, "Cm2", false);
data.AddData(CmValues, GUIColors.GetColor(2), Localizer.Format("FARAbbrevCm"), true);
data.AddData(LDValues2, GUIColors.GetColor(3) * 0.5f, "L/D2", false);
data.AddData(LDValues, GUIColors.GetColor(3), Localizer.Format("FARAbbrevL_D"), true);
data.exportdata.AddSizeVariables(_instantCondition, pitch, flapSetting, spoilers);
data.exportdata.AddAoASweepXVariable(machNumber, AlphaValues);
data.exportdata.AddYVariables(data);
return(data);
}
