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 StabilityDerivExportOutput CalculateStabilityDerivs(CelestialBody body, double alt, double machNumber, int flapSetting, bool spoilers, double beta, double phi) { double pressure = body.GetPressure(alt); double temperature = body.GetTemperature(alt); double density = body.GetDensity(pressure, temperature); double sspeed = body.GetSpeedOfSound(pressure, density); double u0 = sspeed * machNumber; double q = u0 * u0 * density * 0.5f; Vector3d CoM; double mass, area, MAC, b; _instantCondition.GetCoMAndSize(out CoM, out mass, out area, out MAC, out b); double effectiveG = _instantCondition.CalculateEffectiveGravity(body, alt, u0); double neededCl = effectiveG * mass / (q * area); InstantConditionSimVars iterationSimVars = new InstantConditionSimVars(_instantCondition, body, alt, machNumber, neededCl, beta, phi, flapSetting, spoilers); InstantConditionSimInput nominalInput; InstantConditionSimOutput nominalOutput; InstantConditionSimIterationResult stableCondition = iterationSimVars.IterateForAlphaAndPitch(out nominalInput, out nominalOutput); InstantConditionSimInput input = nominalInput.Clone(); InstantConditionSimOutput pertOutput; double[] derivatives = new double[27]; // update size (in practice MAC and b) to match stableCondition _instantCondition.GetCoMAndSize(out CoM, out mass, out area, out MAC, out b); double Ix, Iy, Iz; double Ixy, Iyz, Ixz; _instantCondition.GetInertia(CoM, out Ix, out Iy, out Iz, out Ixy, out Iyz, out Ixz); input.alpha = stableCondition.stableAoA + 2; iterationSimVars.ResetAndGetClCdCmSteady(input, out pertOutput); // Rodhern: A change is made to the Xw formula. Theoretically doing " -= nominalOutput.Cl" is the most 'correct', // it does however in some way mix the Cd value measured at 'stableAoA + 2' with a Cl value measured at 'StableAoA'. // Because Cl and Cd are very AoA-dependent, the asymmetrical measurement (AoA+=[0;2]) is quite affected. double pertOutCl = pertOutput.Cl; pertOutput.Cl = (pertOutput.Cl - nominalOutput.Cl) / (2 * FARMathUtil.deg2rad); //vert vel derivs pertOutput.Cd = (pertOutput.Cd - nominalOutput.Cd) / (2 * FARMathUtil.deg2rad); pertOutput.Cm = (pertOutput.Cm - nominalOutput.Cm) / (2 * FARMathUtil.deg2rad); pertOutput.Cl += nominalOutput.Cd; pertOutput.Cd -= pertOutCl; // Rodhern: Convergence is worse, but possibly the numerical value is more useful this way. pertOutput.Cl *= -q * area / (mass * u0); pertOutput.Cd *= -q * area / (mass * u0); pertOutput.Cm *= q * area * MAC / (Iy * u0); derivatives[3] = pertOutput.Cl; //Zw derivatives[4] = pertOutput.Cd; //Xw derivatives[5] = pertOutput.Cm; //Mw input.alpha = stableCondition.stableAoA; input.fltenv.MachNumber = machNumber + 0.05; iterationSimVars.ResetAndGetClCdCmSteady(input, out pertOutput); pertOutput.Cl = (pertOutput.Cl - nominalOutput.Cl) / 0.05 * machNumber; //fwd vel derivs pertOutput.Cd = (pertOutput.Cd - nominalOutput.Cd) / 0.05 * machNumber; pertOutput.Cm = (pertOutput.Cm - nominalOutput.Cm) / 0.05 * machNumber; pertOutput.Cl += 2 * nominalOutput.Cl; pertOutput.Cd += 2 * nominalOutput.Cd; pertOutput.Cm += 2 * nominalOutput.Cm; pertOutput.Cl *= -q * area / (mass * u0); pertOutput.Cd *= -q * area / (mass * u0); pertOutput.Cm *= q * area * MAC / (Iy * u0); derivatives[6] = pertOutput.Cl; //Zu derivatives[7] = pertOutput.Cd; //Xu derivatives[8] = pertOutput.Cm; //Mu input.fltenv.MachNumber = machNumber; input.alphaDot = -3; iterationSimVars.ResetAndGetClCdCmSteady(input, out pertOutput); pertOutput.Cl = (pertOutput.Cl - nominalOutput.Cl) / (3 * FARMathUtil.deg2rad); //pitch rate derivs pertOutput.Cd = (pertOutput.Cd - nominalOutput.Cd) / (3 * FARMathUtil.deg2rad); pertOutput.Cm = (pertOutput.Cm - nominalOutput.Cm) / (3 * FARMathUtil.deg2rad); pertOutput.Cl *= -q * area / mass; pertOutput.Cd *= -q * area / mass; pertOutput.Cm *= q * area * MAC / Iy; derivatives[9] = pertOutput.Cl; //Zq derivatives[10] = pertOutput.Cd; //Xq derivatives[11] = pertOutput.Cm; //Mq input.alphaDot = 0; double pitchDelta = (stableCondition.stablePitchValue > 0) ? -0.1 : 0.1; input.pitchValue = stableCondition.stablePitchValue + pitchDelta; iterationSimVars.ResetAndGetClCdCmSteady(input, out pertOutput); pertOutput.Cl = (pertOutput.Cl - nominalOutput.Cl) / pitchDelta; //elevator derivs pertOutput.Cd = (pertOutput.Cd - nominalOutput.Cd) / pitchDelta; pertOutput.Cm = (pertOutput.Cm - nominalOutput.Cm) / pitchDelta; pertOutput.Cl *= -q * area / mass; // Rodhern: Replaced 'q' by '-q', so that formulas pertOutput.Cd *= -q * area / mass; // for Ze and Xe match those for Zu and Xu. pertOutput.Cm *= q * area * MAC / Iy; derivatives[12] = pertOutput.Cl; //Ze derivatives[13] = pertOutput.Cd; //Xe derivatives[14] = pertOutput.Cm; //Me input.pitchValue = stableCondition.stablePitchValue; input.beta = (beta + 2); iterationSimVars.ResetAndGetClCdCmSteady(input, out pertOutput); pertOutput.Cy = (pertOutput.Cy - nominalOutput.Cy) / (2 * FARMathUtil.deg2rad); //sideslip angle derivs pertOutput.Cn = (pertOutput.Cn - nominalOutput.Cn) / (2 * FARMathUtil.deg2rad); pertOutput.C_roll = (pertOutput.C_roll - nominalOutput.C_roll) / (2 * FARMathUtil.deg2rad); pertOutput.Cy *= q * area / mass; pertOutput.Cn *= q * area * b / Iz; pertOutput.C_roll *= q * area * b / Ix; derivatives[15] = pertOutput.Cy; //Yb derivatives[17] = pertOutput.Cn; //Nb derivatives[16] = pertOutput.C_roll; //Lb input.beta = beta; input.phiDot = -3; iterationSimVars.ResetAndGetClCdCmSteady(input, out pertOutput); pertOutput.Cy = (pertOutput.Cy - nominalOutput.Cy) / (3 * FARMathUtil.deg2rad); //roll rate derivs pertOutput.Cn = (pertOutput.Cn - nominalOutput.Cn) / (3 * FARMathUtil.deg2rad); pertOutput.C_roll = (pertOutput.C_roll - nominalOutput.C_roll) / (3 * FARMathUtil.deg2rad); pertOutput.Cy *= q * area / mass; pertOutput.Cn *= q * area * b / Iz; pertOutput.C_roll *= q * area * b / Ix; derivatives[18] = pertOutput.Cy; //Yp derivatives[20] = pertOutput.Cn; //Np derivatives[19] = pertOutput.C_roll; //Lp input.phiDot = 0; input.betaDot = -3; iterationSimVars.ResetAndGetClCdCmSteady(input, out pertOutput); pertOutput.Cy = (pertOutput.Cy - nominalOutput.Cy) / (3 * FARMathUtil.deg2rad); //yaw rate derivs pertOutput.Cn = (pertOutput.Cn - nominalOutput.Cn) / (3 * FARMathUtil.deg2rad); pertOutput.C_roll = (pertOutput.C_roll - nominalOutput.C_roll) / (3 * FARMathUtil.deg2rad); pertOutput.Cy *= q * area / mass; pertOutput.Cn *= q * area * b / Iz; pertOutput.C_roll *= q * area * b / Ix; derivatives[21] = pertOutput.Cy; //Yr derivatives[23] = pertOutput.Cn; //Nr derivatives[22] = pertOutput.C_roll; //Lr input = new InstantConditionSimInput(body); // Reset to (an artificial) default condition _instantCondition.ResetClCdCmSteady(CoM, input); // Assign values to output variables StabilityDerivOutput stabDerivOutput = new StabilityDerivOutput(stableCondition, derivatives); stabDerivOutput.nominalVelocity = u0; stabDerivOutput.altitude = alt; stabDerivOutput.body = body; stabDerivOutput.b = b; stabDerivOutput.MAC = MAC; stabDerivOutput.area = area; stabDerivOutput.stabDerivs[0] = Ix; stabDerivOutput.stabDerivs[1] = Iy; stabDerivOutput.stabDerivs[2] = Iz; stabDerivOutput.stabDerivs[24] = Ixy; stabDerivOutput.stabDerivs[25] = Iyz; stabDerivOutput.stabDerivs[26] = Ixz; // Assign values to export variables StabilityDerivExportVariables stabDerivExport = new StabilityDerivExportVariables(); stabDerivExport.craftmass = mass; stabDerivExport.envpressure = pressure; stabDerivExport.envtemperature = temperature; stabDerivExport.envdensity = density; stabDerivExport.envsoundspeed = sspeed; stabDerivExport.envg = _instantCondition.CalculateAccelerationDueToGravity(body, alt); stabDerivExport.sitmach = machNumber; stabDerivExport.sitdynpres = q; stabDerivExport.siteffg = _instantCondition.CalculateEffectiveGravity(body, alt, u0); return(new StabilityDerivExportOutput(stabDerivOutput, stabDerivExport)); }
public void ResetAndGetClCdCmSteady(InstantConditionSimInput input, out InstantConditionSimOutput output) { parent.ResetClCdCmSteady(CoM, input); parent.GetClCdCmSteady(input, out output, true, false); }