public void organiseData() {
// ok, we need to collate the data
data = new HashMap<String, ICollection>();
final CollectionComplianceTests tests = new CollectionComplianceTests();
// ok, transmitter data
data.put(TX + "FREQ", tests.someHave(_tx, Frequency.UNIT.getDimension(), true));
data.put(TX + "COURSE", tests.someHave(_tx, SI.RADIAN.getDimension(), true));
data.put(TX + "SPEED", tests.someHave(_tx, METRE.divide(SECOND).getDimension(), true));
data.put(TX + "LOC", tests.someHaveLocation(_tx));
// and the receiver
data.put(RX + "COURSE", tests.someHave(_rx, SI.RADIAN.getDimension(), true));
data.put(RX + "SPEED", tests.someHave(_rx, METRE.divide(SECOND).getDimension(), true));
data.put(RX + "LOC", tests.someHaveLocation(_rx));
// and the sound speed
data.put(
"SOUND_SPEED", tests.someHave(getInputs(), METRE.divide(SECOND).getDimension(), false));
}
private void initializeAerodynamics(Airfoil airf, AirfoilEnum airfoilName) {
switch (airfoilName) {
case NACA23_018:
_id = airf.getId() + "1" + idCounter + "99";
idCounter++;
airf.setName(AirfoilEnum.NACA23_018);
_theAirfoil = airf;
geometry = airf.getGeometry();
_alphaZeroLift = Amount.valueOf(Math.toRadians(-1.2), SI.RADIAN);
_clAlpha = Amount.valueOf(6.3, SI.RADIAN.inverse());
_alphaStar = Amount.valueOf(Math.toRadians(9.5), SI.RADIAN); // end-of-linearity
_clStar = 1.3;
_alphaStall = Amount.valueOf(Math.toRadians(16.0), SI.RADIAN);
_clMax = 1.65; // 1.8;
_cdMin = 0.00675;
_clAtCdMin = 0.3;
_kFactorDragPolar = 0.004;
_aerodynamicCenterX = 0.243;
_cmAC = -0.02;
_cmACStall = -0.09;
_cmAlphaAC = 0.;
calculateMachCr = new CalculateMachCr();
calculateCdWaveDrag = new CalculateCdWaveDrag();
break;
case NACA23_015:
airf.setName(AirfoilEnum.NACA23_015);
_id = airf.getId() + "1" + idCounter + "99";
idCounter++;
_theAirfoil = airf;
geometry = airf.getGeometry();
_alphaZeroLift = Amount.valueOf(Math.toRadians(-1.1), SI.RADIAN);
_clAlpha = Amount.valueOf(6.3, SI.RADIAN.inverse());
_alphaStar = Amount.valueOf(Math.toRadians(10), SI.RADIAN); // end-of-linearity
_clStar = 1.2;
_alphaStall = Amount.valueOf(Math.toRadians(18.0), SI.RADIAN);
_clMax = 1.7; // 1.6;
_cdMin = 0.00625;
_clAtCdMin = 0.1;
_kFactorDragPolar = 0.004;
_aerodynamicCenterX = 0.243;
_cmAC = -0.02;
_cmACStall = -0.07;
_cmAlphaAC = 0.;
calculateMachCr = new CalculateMachCr();
calculateCdWaveDrag = new CalculateCdWaveDrag();
break;
case NACA23_012:
airf.setName(AirfoilEnum.NACA23_012);
_id = airf.getId() + "1" + idCounter + "99";
idCounter++;
_theAirfoil = airf;
geometry = airf.getGeometry();
_alphaZeroLift = Amount.valueOf(Math.toRadians(-1.32), SI.RADIAN);
_clAlpha = Amount.valueOf(6.3, SI.RADIAN.inverse());
_alphaStar = Amount.valueOf(Math.toRadians(14), SI.RADIAN); // end-of-linearity
_clStar = 1.6;
_alphaStall = Amount.valueOf(Math.toRadians(18), SI.RADIAN);
_clMax = 1.8; // 1.5;
_cdMin = 0.00575;
_clAtCdMin = 0.23;
_kFactorDragPolar = 0.004;
_aerodynamicCenterX = 0.247;
_cmAC = -0.03;
_cmACStall = -0.09;
_cmAlphaAC = 0.;
calculateMachCr = new CalculateMachCr();
calculateCdWaveDrag = new CalculateCdWaveDrag();
break;
case NACA65_209:
_id = airf.getId() + "1" + idCounter + "99";
idCounter++;
_theAirfoil = airf;
geometry = airf.getGeometry();
_alphaZeroLift = Amount.valueOf(Math.toRadians(-1.3), SI.RADIAN);
_clAlpha = Amount.valueOf(5.96, SI.RADIAN.inverse());
_alphaStar = Amount.valueOf(Math.toRadians(11), SI.RADIAN); // end-of-linearity
_clStar = 1.1;
_alphaStall = Amount.valueOf(Math.toRadians(17.0), SI.RADIAN);
_clMax = 1.6;
_cdMin = 0.025;
_clAtCdMin = 0.2;
_kFactorDragPolar = 0.0035;
_aerodynamicCenterX = 0.25;
_cmAC = -0.07;
_cmACStall = -0.09;
_cmAlphaAC = 0.;
calculateMachCr = new CalculateMachCr();
calculateCdWaveDrag = new CalculateCdWaveDrag();
break;
case NACA65_206:
_id = airf.getId() + "1" + idCounter + "99";
idCounter++;
_theAirfoil = airf;
geometry = airf.getGeometry();
_alphaZeroLift = Amount.valueOf(Math.toRadians(-1.4), SI.RADIAN);
_clAlpha = Amount.valueOf(6.13, SI.RADIAN.inverse());
_alphaStar = Amount.valueOf(Math.toRadians(10.0), SI.RADIAN); // end-of-linearity
_clStar = _clAlpha.getEstimatedValue() * _alphaStar.getEstimatedValue();
_alphaStall = Amount.valueOf(Math.toRadians(15.0), SI.RADIAN);
_clMax = 1.3;
_cdMin = 0.025;
_clAtCdMin = 0.2;
_kFactorDragPolar = 0.0035;
_aerodynamicCenterX = 0.25;
_cmAC = -0.07;
_cmACStall = -0.09;
_cmAlphaAC = 0.;
calculateMachCr = new CalculateMachCr();
calculateCdWaveDrag = new CalculateCdWaveDrag();
break;
case NACA0012:
airf.setName(AirfoilEnum.NACA0012);
_id = airf.getId() + "1" + idCounter + "99";
idCounter++;
_theAirfoil = airf;
geometry = airf.getGeometry();
_alphaZeroLift = Amount.valueOf(Math.toRadians(0), SI.RADIAN);
_clAlpha = Amount.valueOf(6.92, SI.RADIAN.inverse());
_alphaStar = Amount.valueOf(Math.toRadians(11), SI.RADIAN); // end-of-linearity
_clStar = 1.23;
_alphaStall = Amount.valueOf(Math.toRadians(20.1), SI.RADIAN);
_clMax = 1.86; // 1.5;
_cdMin = 0.0055;
_clAtCdMin = 0.0;
_kFactorDragPolar = 0.0035;
_aerodynamicCenterX = 0.25;
_cmAC = 0.0;
_cmACStall = -0.09;
_cmAlphaAC = 0.;
calculateMachCr = new CalculateMachCr();
calculateCdWaveDrag = new CalculateCdWaveDrag();
break;
case DFVLR_R4:
airf.setName(AirfoilEnum.DFVLR_R4);
_id = airf.getId() + "1" + idCounter + "99";
idCounter++;
_theAirfoil = airf;
geometry = airf.getGeometry();
_alphaZeroLift = Amount.valueOf(Math.toRadians(-3.75), SI.RADIAN);
_clAlpha = Amount.valueOf(6.3, SI.RADIAN.inverse());
_alphaStar = Amount.valueOf(Math.toRadians(11), SI.RADIAN); // end-of-linearity
_clStar = 1.53;
_alphaStall = Amount.valueOf(Math.toRadians(16.75), SI.RADIAN);
_clMax = 1.7671; // 1.5;
_cdMin = 0.0056;
_clAtCdMin = 0.0;
_kFactorDragPolar = 0.075;
_aerodynamicCenterX = 0.25;
_cmAC = -0.1168;
_cmACStall = -0.0515;
_cmAlphaAC = 0.0015;
calculateMachCr = new CalculateMachCr();
calculateCdWaveDrag = new CalculateCdWaveDrag();
break;
default:
break;
}
}