/**
* This function plots the airfoil drag polar using a parabolic approssimation.
*
* @author Manuela Ruocco
*/
public void plotPolar() {
System.out.println("\n \n-----------------------------------------------------");
System.out.println("STARTING PLOT AIRFOIL DRAG POLAR");
System.out.println("-----------------------------------------------------");
MyArray alphaArray = new MyArray();
int _numberOfAlpha = 40;
double[] cdArrayPolar = new double[_numberOfAlpha];
double[] clArrayPolar = new double[_numberOfAlpha];
Amount<Angle> alphaActualAmount;
Amount<Angle> alphaStart = Amount.valueOf(toRadians(-6.), SI.RADIAN);
Amount<Angle> alphaEnd = Amount.valueOf(toRadians(12.), SI.RADIAN);
alphaArray.setDouble(
MyArrayUtils.linspace(
alphaStart.getEstimatedValue(), alphaEnd.getEstimatedValue(), _numberOfAlpha));
String folderPathPolar =
MyConfiguration.currentDirectoryString + File.separator + "out" + File.separator;
String subfolderPathPolar =
JPADStaticWriteUtils.createNewFolder(folderPathPolar + "Polar_Airfoil" + File.separator);
for (int i = 0; i < _numberOfAlpha; i++) {
alphaActualAmount = Amount.valueOf(alphaArray.get(i), SI.RADIAN);
clArrayPolar[i] = calculateClAtAlpha(alphaActualAmount.getEstimatedValue());
cdArrayPolar[i] = calculateCdAtAlpha(alphaActualAmount);
}
MyChartToFileUtils.plotNoLegend(
cdArrayPolar,
clArrayPolar,
null,
null,
null,
null,
"Cd",
"Cl",
"",
"",
subfolderPathPolar,
"Polar_Airfoil ");
System.out.println("\n \n-----------------------------------------------------");
System.out.println("DONE");
System.out.println("-----------------------------------------------------");
}
public void plotClvsAlpha(String subfolderPath, String name) {
System.out.println("\n \n-----------------------------------------------------");
System.out.println("STARTING PLOT AIRFOIL CL vs ALPHA CURVE " + name);
System.out.println("-----------------------------------------------------");
MyArray alphaArray = new MyArray();
int _numberOfAlpha = 60;
double[] clArray = new double[_numberOfAlpha];
double[] alphaArrayDeg = new double[_numberOfAlpha];
Amount<Angle> alphaActualAmount;
Amount<Angle> alphaStart = Amount.valueOf(toRadians(-6.), SI.RADIAN);
Amount<Angle> alphaEnd = Amount.valueOf(toRadians(25.0), SI.RADIAN);
alphaArray.setDouble(
MyArrayUtils.linspace(
alphaStart.getEstimatedValue(), alphaEnd.getEstimatedValue(), _numberOfAlpha));
for (int i = 0; i < _numberOfAlpha; i++) {
alphaActualAmount = Amount.valueOf(alphaArray.get(i), SI.RADIAN);
clArray[i] = calculateClAtAlpha(alphaActualAmount.getEstimatedValue());
alphaArrayDeg[i] = alphaActualAmount.to(NonSI.DEGREE_ANGLE).getEstimatedValue();
}
MyChartToFileUtils.plotNoLegend(
alphaArrayDeg,
clArray,
null,
null,
null,
null,
"alpha",
"CL",
"deg",
"",
subfolderPath,
"CL vs alpha Airfoil" + name);
System.out.println("-----------------------------------------------------");
System.out.println("\n DONE");
System.out.println("-----------------------------------------------------");
}
public static List<Double> calcCmDistributionLiftingSurfaceWithIntegral(
NasaBlackwell theNasaBlackwellCalculator,
Amount<Angle> angleOfAttack,
List<Amount<Length>> liftingSurfaceDimensionalY,
List<Double> liftingSurfaceCl0Distribution, // all distributions must have the same length!!
List<Double> liftingSurfaceCLAlphaDegDistribution,
List<Double> liftingSurfaceCmACDistribution,
List<Double> liftingSurfaceXACadimensionalDistribution,
List<Amount<Length>> liftingSurfaceChordDistribution,
List<Amount<Length>> liftingSurfaceXLEDistribution,
List<List<Double>>
airfoilClMatrix, // this is a list of list. each list is referred to an airfoil along the
// semispan
List<Amount<Angle>>
anglesOfAttackClMatrix, // references angle of attack of the list of list airfoilClMatrix
Amount<Length> momentumPole // referred to the origin of LRF
) {
List<Double> cmDistribution = new ArrayList<>();
double[] distancesArrayAC,
clDistribution,
alphaDistribution,
clInducedDistributionAtAlphaNew,
xcPfracC;
int numberOfPointSemiSpanWise = liftingSurfaceCl0Distribution.size();
clDistribution = new double[numberOfPointSemiSpanWise];
alphaDistribution = new double[numberOfPointSemiSpanWise];
clInducedDistributionAtAlphaNew = new double[numberOfPointSemiSpanWise];
distancesArrayAC = new double[numberOfPointSemiSpanWise];
xcPfracC = new double[numberOfPointSemiSpanWise];
theNasaBlackwellCalculator.calculate(angleOfAttack);
clDistribution = theNasaBlackwellCalculator.getClTotalDistribution().toArray();
for (int ii = 0; ii < numberOfPointSemiSpanWise; ii++) {
alphaDistribution[ii] =
(clDistribution[ii] - liftingSurfaceCl0Distribution.get(ii))
/ liftingSurfaceCLAlphaDegDistribution.get(ii);
if (alphaDistribution[ii] < angleOfAttack.doubleValue(NonSI.DEGREE_ANGLE)) {
clInducedDistributionAtAlphaNew[ii] =
liftingSurfaceCLAlphaDegDistribution.get(ii) * alphaDistribution[ii]
+ liftingSurfaceCl0Distribution.get(ii);
} else {
clInducedDistributionAtAlphaNew[ii] =
MyMathUtils.getInterpolatedValue1DLinear(
MyArrayUtils.convertListOfAmountTodoubleArray(anglesOfAttackClMatrix),
MyArrayUtils.convertToDoublePrimitive(
MyArrayUtils.convertListOfDoubleToDoubleArray(airfoilClMatrix.get(ii))),
alphaDistribution[ii]);
}
xcPfracC[ii] =
liftingSurfaceXACadimensionalDistribution.get(ii)
- (liftingSurfaceCmACDistribution.get(ii) / clInducedDistributionAtAlphaNew[ii]);
distancesArrayAC[ii] =
momentumPole.doubleValue(SI.METER)
- (liftingSurfaceXLEDistribution.get(ii).doubleValue(SI.METER)
+ (xcPfracC[ii] * liftingSurfaceChordDistribution.get(ii).doubleValue(SI.METER)));
cmDistribution.add(
ii,
clInducedDistributionAtAlphaNew[ii]
* (distancesArrayAC[ii]
/ liftingSurfaceChordDistribution.get(ii).doubleValue(SI.METER)));
}
cmDistribution.set(numberOfPointSemiSpanWise - 1, 0.);
return cmDistribution;
}
public static List<Double> calcCMLiftingSurfaceWithIntegralACVariable(
NasaBlackwell theNasaBlackwellCalculator,
List<Amount<Angle>> anglesOfAttack,
Amount<Length> liftingSurfaceMAC,
List<Amount<Length>> liftingSurfaceDimensionalY,
List<Double> liftingSurfaceCl0Distribution, // all distributions must have the same length!!
List<Double> liftingSurfaceCLAlphaDegDistribution,
List<Double> liftingSurfaceCLforCMMatrix,
List<List<Double>> liftingSurfaceCmACDistribution,
List<Double> liftingSurfaceXACadimensionalDistribution,
List<Amount<Length>> liftingSurfaceChordDistribution,
List<Amount<Length>> liftingSurfaceXLEDistribution,
List<List<Double>>
airfoilClMatrix, // this is a list of list. each list is referred to an airfoil along the
// semispan
List<Amount<Angle>>
anglesOfAttackClMatrix, // references angle of attack of the list of list airfoilClMatrix
Amount<Area> liftingSurfaceArea,
Amount<Length> momentumPole // referred to the origin of LRF
) {
List<Double> liftingSurfaceMomentCoefficient = new ArrayList<>();
double[] distancesArrayAC,
clDistribution,
alphaDistribution,
clInducedDistributionAtAlphaNew,
cmDistribution,
cCm,
xcPfracC;
double cmActual;
int numberOfAlphas = anglesOfAttack.size();
int numberOfPointSemiSpanWise = liftingSurfaceCl0Distribution.size();
for (int i = 0; i < numberOfAlphas; i++) {
clDistribution = new double[numberOfPointSemiSpanWise];
alphaDistribution = new double[numberOfPointSemiSpanWise];
clInducedDistributionAtAlphaNew = new double[numberOfPointSemiSpanWise];
distancesArrayAC = new double[numberOfPointSemiSpanWise];
cmDistribution = new double[numberOfPointSemiSpanWise];
cCm = new double[numberOfPointSemiSpanWise];
xcPfracC = new double[numberOfPointSemiSpanWise];
theNasaBlackwellCalculator.calculate(anglesOfAttack.get(i));
clDistribution = theNasaBlackwellCalculator.getClTotalDistribution().toArray();
// clInducedDistributionAtAlphaNew = clDistribution;
for (int ii = 0; ii < numberOfPointSemiSpanWise; ii++) {
alphaDistribution[ii] =
(clDistribution[ii] - liftingSurfaceCl0Distribution.get(ii))
/ liftingSurfaceCLAlphaDegDistribution.get(ii);
if (alphaDistribution[ii] < anglesOfAttack.get(0).doubleValue(NonSI.DEGREE_ANGLE)) {
clInducedDistributionAtAlphaNew[ii] =
liftingSurfaceCLAlphaDegDistribution.get(ii) * alphaDistribution[ii]
+ liftingSurfaceCl0Distribution.get(ii);
} else {
clInducedDistributionAtAlphaNew[ii] =
MyMathUtils.getInterpolatedValue1DLinear(
MyArrayUtils.convertListOfAmountTodoubleArray(anglesOfAttackClMatrix),
MyArrayUtils.convertToDoublePrimitive(
MyArrayUtils.convertListOfDoubleToDoubleArray(airfoilClMatrix.get(ii))),
alphaDistribution[ii]);
}
cmActual =
MyMathUtils.getInterpolatedValue1DLinear(
MyArrayUtils.convertToDoublePrimitive(liftingSurfaceCLforCMMatrix),
MyArrayUtils.convertToDoublePrimitive(liftingSurfaceCmACDistribution.get(ii)),
clInducedDistributionAtAlphaNew[ii]);
// xcPfracC[ii] = liftingSurfaceXACadimensionalDistribution.get(ii) -
// (cmActual/
// clInducedDistributionAtAlphaNew[ii]);
xcPfracC[ii] = 0.25 - (cmActual / clInducedDistributionAtAlphaNew[ii]);
distancesArrayAC[ii] =
momentumPole.doubleValue(SI.METER)
- (liftingSurfaceXLEDistribution.get(ii).doubleValue(SI.METER)
+ (xcPfracC[ii]
* liftingSurfaceChordDistribution.get(ii).doubleValue(SI.METER)));
cmDistribution[ii] =
clInducedDistributionAtAlphaNew[ii]
* (distancesArrayAC[ii]
/ liftingSurfaceChordDistribution.get(ii).doubleValue(SI.METER));
cCm[ii] =
cmDistribution[ii]
* liftingSurfaceChordDistribution.get(ii).doubleValue(SI.METER)
* liftingSurfaceChordDistribution.get(ii).doubleValue(SI.METER);
}
// System.out.println(" distance " + Arrays.toString(distancesArrayAC));
// System.out.println(" xcp " + Arrays.toString(xcPfracC));
// System.out.println(" cl " + Arrays.toString(clDistribution));
// System.out.println(" cl new " + Arrays.toString(clInducedDistributionAtAlphaNew));
// System.out.println(" cm " + Arrays.toString(cmDistribution) );
// System.out.println(" ccm " + Arrays.toString(cCm));
cCm[numberOfPointSemiSpanWise - 1] = 0;
liftingSurfaceMomentCoefficient.add(
i,
((2
/ (liftingSurfaceArea.doubleValue(SI.SQUARE_METRE)
* liftingSurfaceMAC.doubleValue(SI.METER)))
* MyMathUtils.integrate1DSimpsonSpline(
MyArrayUtils.convertListOfAmountTodoubleArray(liftingSurfaceDimensionalY), cCm)));
}
return liftingSurfaceMomentCoefficient;
}
