diff --git a/aerodynamic_analysis/src/methods/viscDragForTandem.cpp b/aerodynamic_analysis/src/methods/viscDragForTandem.cpp
index 6974a1feff44f378257caac132ecc9171d4f870d..81ed5102ab5173d709abac7570ea1ea79b47499f 100644
--- a/aerodynamic_analysis/src/methods/viscDragForTandem.cpp
+++ b/aerodynamic_analysis/src/methods/viscDragForTandem.cpp
@@ -59,14 +59,14 @@ using std::vector;
*/
viscDragForTandemInitialization::viscDragForTandemInitialization()
:
- calculateWing(false),
+ calculateFrontWing(false),
calculateFuselage(false),
calculateVTP(false),
calculateBackWing(false),
calculateNacelles(false),
calculateMisc(false),
manualTransitionLocation(false),
- transitionLocationWing(NAN),
+ transitionLocationFrontWing(NAN),
transitionLocationBackWing(NAN),
transitionLocationVTP(NAN),
doCalibration(false),
@@ -76,20 +76,20 @@ viscDragForTandemInitialization::viscDragForTandemInitialization()
CDvisc_CDsum_lowMa(NAN),
CDvisc_CLfact_lowMa(NAN),
CDvisc_CLexp_lowMa(NAN),
- jetEngine(false) {
+ jetEngine(false) { // TODO kayra: Tandem de nereye ve ne kadar koyacagimiz daha belli degil
}
viscDragForTandem::viscDragForTandem(const std::shared_ptr<RuntimeIO>& rtIO, const viscDragForTandemInitialization& viscDragInit)
:
// the following variables need to be initialized externally
- calculateWing(viscDragInit.calculateWing),
+ calculateFrontWing(viscDragInit.calculateFrontWing),
calculateFuselage(viscDragInit.calculateFuselage),
calculateVTP(viscDragInit.calculateVTP),
calculateBackWing(viscDragInit.calculateBackWing),
calculateNacelles(viscDragInit.calculateNacelles),
calculateMisc(viscDragInit.calculateMisc),
manualTransitionLocation(viscDragInit.manualTransitionLocation),
- transitionLocationWing(viscDragInit.transitionLocationWing),
+ transitionLocationFrontWing(viscDragInit.transitionLocationFrontWing),
transitionLocationBackWing(viscDragInit.transitionLocationBackWing),
transitionLocationVTP(viscDragInit.transitionLocationVTP),
doCalibration(viscDragInit.doCalibration),
@@ -100,14 +100,14 @@ viscDragForTandem::viscDragForTandem(const std::shared_ptr<RuntimeIO>& rtIO, con
CDvisc_CLfact_lowMa(viscDragInit.CDvisc_CLfact_lowMa),
CDvisc_CLexp_lowMa(viscDragInit.CDvisc_CLexp_lowMa),
jetEngine(viscDragInit.jetEngine),
- Sref_Wing(NAN),
- Swet_Wing(NAN),
- MAC_Wing(NAN),
- avgTtoC_Wing(NAN),
- mXtoC_Wing(NAN),
- eta_ref_Wing(NAN),
- phiAtmXtoC_Wing(NAN),
- QC_Wing(NAN),
+ Sref_FrontWing(NAN),
+ Swet_FrontWing(NAN),
+ MAC_FrontWing(NAN),
+ avgTtoC_FrontWing(NAN),
+ mXtoC_FrontWing(NAN),
+ eta_ref_FrontWing(NAN),
+ phiAtmXtoC_FrontWing(NAN),
+ QC_FrontWing(NAN),
Sref_BackWing(NAN),
Swet_BackWing(NAN),
MAC_BackWing(NAN),
@@ -135,8 +135,8 @@ viscDragForTandem::viscDragForTandem(const std::shared_ptr<RuntimeIO>& rtIO, con
maxHeightNacelles(NAN),
QC_Nacelles(NAN),
factorProtuberances(NAN) {
- if (calculateWing) {
- theAircraftComponents.myWing = viscDragInit.theWing;
+ if (calculateFrontWing) {
+ theAircraftComponents.myFrontWing = viscDragInit.theFrontWing;
}
if (calculateFuselage) {
theAircraftComponents.myFuselage = viscDragInit.theFuselage;
@@ -151,7 +151,7 @@ viscDragForTandem::viscDragForTandem(const std::shared_ptr<RuntimeIO>& rtIO, con
theAircraftComponents.myVTP = viscDragInit.theVTP;
}
if (!manualTransitionLocation) {
- transitionLocationWing = 0.0;
+ transitionLocationFrontWing = 0.0;
transitionLocationBackWing = 0.0;
transitionLocationVTP = 0.0;
}
@@ -159,32 +159,32 @@ viscDragForTandem::viscDragForTandem(const std::shared_ptr<RuntimeIO>& rtIO, con
void viscDragForTandem::preprocessGeometry() {
myRuntimeInfo->debug << "viscDragForTandem: preprocess the aircraft geometry" << endl;
- if (calculateWing) {
- Sref_Wing = geom2::measure::reference_area(theAircraftComponents.myWing);
- Swet_Wing = geom2::measure::area(theAircraftComponents.myWing);
- MAC_Wing = geom2::measure::mean_aerodynamic_chord(theAircraftComponents.myWing);
- avgTtoC_Wing = getAverageTtoC(theAircraftComponents.myWing);
- mXtoC_Wing = 0.5; // Assumption by Raymer for chordwise location of airfoil maximum thickness point for high-speed airfoils
- eta_ref_Wing = 0.65; // Reference position used for local sweep <- cant find this value in the source
- phiAtmXtoC_Wing = getLocalSweep(theAircraftComponents.myWing, eta_ref_Wing * getHalfSpan(theAircraftComponents.myWing), mXtoC_Wing, "RADIAN");
- QC_Wing = 1.; // Assumtion for high, mid, and well fitted low wing
+ if (calculateFrontWing) {
+ Sref_FrontWing = geom2::measure::reference_area(theAircraftComponents.myFrontWing);
+ Swet_FrontWing = geom2::measure::area(theAircraftComponents.myFrontWing);
+ MAC_FrontWing = geom2::measure::mean_aerodynamic_chord(theAircraftComponents.myFrontWing);
+ avgTtoC_FrontWing = getAverageTtoC(theAircraftComponents.myFrontWing);
+ mXtoC_FrontWing = 0.5; // Assumption by Raymer for chordwise location of airfoil maximum thickness point for high-speed airfoils
+ eta_ref_FrontWing = 0.65; // Reference position used for local sweep <- cant find this value in the source
+ phiAtmXtoC_FrontWing = getLocalSweep(theAircraftComponents.myFrontWing, eta_ref_FrontWing * getHalfSpan(theAircraftComponents.myFrontWing), mXtoC_FrontWing, "RADIAN");
+ QC_FrontWing = 1.; // Assumtion for high, mid, and well fitted low wing
/*
// Wetted Surface
if (!myAcftPt->theFuselage.empty()) {
- wFuselage = myAcftPt->theFuselage.at(0).getLocalWidth(myAcftPt->theWing.at(i).referencePtx);
- hFuselage = myAcftPt->theFuselage.at(0).getLocalHeight(myAcftPt->theWing.at(i).referencePtx);
- zFuselage = myAcftPt->theFuselage.at(0).getLocalOffset(myAcftPt->theWing.at(i).referencePtx);
+ wFuselage = myAcftPt->theFuselage.at(0).getLocalWidth(myAcftPt->theFrontWing.at(i).referencePtx);
+ hFuselage = myAcftPt->theFuselage.at(0).getLocalHeight(myAcftPt->theFrontWing.at(i).referencePtx);
+ zFuselage = myAcftPt->theFuselage.at(0).getLocalOffset(myAcftPt->theFrontWing.at(i).referencePtx);
}
// Check if wing object is located in fuselage
- if (myAcftPt->theWing.at(i).referencePtz < (zFuselage + hFuselage / 2) &&
- myAcftPt->theWing.at(i).referencePtz > (zFuselage - hFuselage / 2)) { // If tailplane Z-coordinate inside fuselage
- Swet.push_back(myAcftPt->theWing.at(i).getWingSurface() - 2.*(wFuselage * myAcftPt->theWing.at(i).l_i_right));
+ if (myAcftPt->theFrontWing.at(i).referencePtz < (zFuselage + hFuselage / 2) &&
+ myAcftPt->theFrontWing.at(i).referencePtz > (zFuselage - hFuselage / 2)) { // If tailplane Z-coordinate inside fuselage
+ Swet.push_back(myAcftPt->theFrontWing.at(i).getWingSurface() - 2.*(wFuselage * myAcftPt->theFrontWing.at(i).l_i_right));
} else {
- Swet.push_back(myAcftPt->theWing.at(i).getWingSurface());
+ Swet.push_back(myAcftPt->theFrontWing.at(i).getWingSurface());
}
*/
}
- if (calculateBackWing) { //TODO kayra: her türlü tandem icin yap bir tane, damit nutzer nicht verwirrt wird.
+ if (calculateBackWing) {
Sref_BackWing = geom2::measure::reference_area(theAircraftComponents.myBackWing);
Swet_BackWing = geom2::measure::area(theAircraftComponents.myBackWing);
MAC_BackWing = geom2::measure::mean_aerodynamic_chord(theAircraftComponents.myBackWing);
@@ -192,7 +192,7 @@ void viscDragForTandem::preprocessGeometry() {
mXtoC_BackWing = 0.5; // Assumption by Raymer for chordwise location of airfoil maximum thickness point for high-speed airfoils BackWing //TODO: kayra
eta_ref_BackWing = 0.65; // Reference position used for local sweep
phiAtmXtoC_BackWing = getLocalSweep(theAircraftComponents.myBackWing, eta_ref_BackWing * getHalfSpan(theAircraftComponents.myBackWing), mXtoC_BackWing, "RADIAN");
- QC_BackWing = 1.04; // Form factor BackWing
+ QC_BackWing = 1.04; // Form factor BackWing TODO kayra: sorun var
}
if (calculateVTP) {
Swet_VTP = geom2::measure::area(theAircraftComponents.myVTP);
@@ -225,7 +225,7 @@ void viscDragForTandem::preprocessGeometry() {
factorProtuberances = 0.07;
}
myRuntimeInfo->out << "Viscous drag calculation by Raymer successfully initialized for:" << endl;
- if (calculateWing)
+ if (calculateFrontWing)
myRuntimeInfo->out << " -FrontWing" << endl;
if (calculateBackWing)
myRuntimeInfo->out << " -BackWing" << endl;
@@ -239,17 +239,17 @@ void viscDragForTandem::preprocessGeometry() {
myRuntimeInfo->out << " -miscellaneous" << endl;
}
-std::vector<double> viscDragForTandem::calculateViscDrag(const Polar& aPolar, const double transitionLocationWing,
+std::vector<double> viscDragForTandem::calculateViscDrag(const Polar& aPolar, const double transitionLocationFrontWing,
const double transitionLocationBackWing, const double transitionLocationVTP) {
// [Ray18] p. 280 ff. (pdf p. 294 ff.)
- if (calculateWing == false) {
+ if (calculateFrontWing == false) { //TODO kayra:sadece bir tanesine bakiyor belki degistirebiliriz
std::stringstream errorMsg;
- errorMsg << "No wing in viscous drag raymer. Unable to calculate drag";
+ errorMsg << "No front wing in viscous drag raymer. Unable to calculate drag";
throwError(__FILE__, __func__, __LINE__, errorMsg.str());
}
- // vector with component order: 0 = Wing, 1 = BackWing, 2 = VTP, 3 = Fuselage, 4 = Nacelles, 5 = Miscellaneous
+ // vector with component order: 0 = FrontWing, 1 = BackWing, 2 = VTP, 3 = Fuselage, 4 = Nacelles, 5 = Miscellaneous
vector <double> theComponentDrags;
- theComponentDrags.push_back(calculateViscDragWing(aPolar, transitionLocationWing));
+ theComponentDrags.push_back(calculateViscDragFrontWing(aPolar, transitionLocationFrontWing));
// calculate BackWing drag if switch is on
if (calculateBackWing) {
theComponentDrags.push_back(calculateViscDragBackWing(aPolar, transitionLocationBackWing));
@@ -293,7 +293,7 @@ std::vector<double> viscDragForTandem::calculateCorrectedViscDrag(const std::vec
std::vector <double> correctedComponentDrags = componentDrags;
if (doCalibration) {
if (aMachNumber > 0.5) {
- correctedComponentDrags.front() += CDvisc_CDsum + CDvisc_CLfact * pow(CL, CDvisc_CLexp);
+ correctedComponentDrags.front() += CDvisc_CDsum + CDvisc_CLfact * pow(CL, CDvisc_CLexp); //TODO kayra
} else if (aMachNumber <= 0.5) {
correctedComponentDrags.front() += CDvisc_CDsum_lowMa + CDvisc_CLfact_lowMa * pow(CL, CDvisc_CLexp_lowMa);
}
@@ -301,25 +301,25 @@ std::vector<double> viscDragForTandem::calculateCorrectedViscDrag(const std::vec
return correctedComponentDrags;
}
-double viscDragForTandem::calculateViscDragWing(const Polar& aPolar, const double transitionLocationWing) {
+double viscDragForTandem::calculateViscDragFrontWing(const Polar& aPolar, const double transitionLocationFrontWing) {
// [Ray18] p. 280 ff. (pdf p. 294 ff.)
- myRuntimeInfo->debug << " - Get viscous drag wing ..." << endl;
- double CDvisc_Wing(0.);
- double reynoldNumberWing = getReynoldsNumber(MAC_Wing, aPolar.altitude, aPolar.MachNumber);
+ myRuntimeInfo->debug << " - Get viscous drag front wing ..." << endl;
+ double CDvisc_FrontWing(0.);
+ double reynoldNumberFrontWing = getReynoldsNumber(MAC_FrontWing, aPolar.altitude, aPolar.MachNumber);
double Cf;
double Cflaminar;
double FF;
// Friction Coefficient (turbulent) for the wing
- Cf = (getFrictionCoefficient(aPolar.MachNumber, reynoldNumberWing));
+ Cf = (getFrictionCoefficient(aPolar.MachNumber, reynoldNumberFrontWing));
// Friction Coefficient (laminar) for the wing
- Cflaminar = (1.328 / sqrt(reynoldNumberWing));
+ Cflaminar = (1.328 / sqrt(reynoldNumberFrontWing));
// Form factor for the components (eq. 12.30)
- FF = (1. + 0.6 / mXtoC_Wing * avgTtoC_Wing + 100.*pow(avgTtoC_Wing, 4.))
- * (1.34 * pow(aPolar.MachNumber, 0.18) * pow(cos(phiAtmXtoC_Wing), 0.28));
+ FF = (1. + 0.6 / mXtoC_FrontWing * avgTtoC_FrontWing + 100.*pow(avgTtoC_FrontWing, 4.))
+ * (1.34 * pow(aPolar.MachNumber, 0.18) * pow(cos(phiAtmXtoC_FrontWing), 0.28));
// fully turbulent for transitionLocation = 0.0
- CDvisc_Wing = (Cflaminar * transitionLocationWing + Cf * (1. - transitionLocationWing))
- * FF * QC_Wing * Swet_Wing / (Sref_Wing + Sref_BackWing);
- return CDvisc_Wing;
+ CDvisc_FrontWing = (Cflaminar * transitionLocationFrontWing + Cf * (1. - transitionLocationFrontWing))
+ * FF * QC_FrontWing * Swet_FrontWing / (Sref_FrontWing + Sref_BackWing);
+ return CDvisc_FrontWing;
}
double viscDragForTandem::calculateViscDragBackWing(const Polar& aPolar, const double transitionLocationBackWing) {
@@ -338,7 +338,7 @@ double viscDragForTandem::calculateViscDragBackWing(const Polar& aPolar, const d
FF = ((1. + 0.6 / mXtoC_BackWing * avgTtoC_BackWing + 100.*pow(avgTtoC_BackWing, 4.))
* (1.34 * pow(aPolar.MachNumber, 0.18) * pow(cos(phiAtmXtoC_BackWing), 0.28)));
CDvisc_BackWing = (Cflaminar * transitionLocationBackWing + Cf * (1. - transitionLocationBackWing))
- * FF * QC_BackWing * Swet_BackWing / (Sref_Wing + Sref_BackWing);
+ * FF * QC_BackWing * Swet_BackWing / (Sref_FrontWing + Sref_BackWing);
return CDvisc_BackWing;
}
@@ -358,7 +358,7 @@ double viscDragForTandem::calculateViscDragVTP(const Polar& aPolar, const double
* (1.34 * pow(aPolar.MachNumber, 0.18) * pow(cos(phiAtmXtoC_VTP), 0.28));
// Store components
CDvisc_VTP = (Cflaminar * transitionLocationVTP + Cf * (1. - transitionLocationVTP))
- * FF * QC_VTP * Swet_VTP / (Sref_Wing + Sref_BackWing);
+ * FF * QC_VTP * Swet_VTP / (Sref_FrontWing + Sref_BackWing);
return CDvisc_VTP;
}
@@ -374,7 +374,7 @@ double viscDragForTandem::calculateViscDragFuselage(const Polar& aPolar) {
// Form factor for fuselage
double f_Fuselage = l_Fuselage / sqrt(maxHeightFuselage * maxWidthFuselage);
FF = 1. + (60. / pow(f_Fuselage, 3.)) + (f_Fuselage / 400.);
- CDvisc_Fuselage = Cf * FF * QC_Fuselage * Swet_Fuselage / (Sref_Wing + Sref_BackWing);
+ CDvisc_Fuselage = Cf * FF * QC_Fuselage * Swet_Fuselage / (Sref_FrontWing + Sref_BackWing);
return CDvisc_Fuselage;
}
@@ -393,7 +393,7 @@ double viscDragForTandem::calculateViscDragNacelles(const Polar& aPolar) {
double f_Nacelles = l_Nacelles / sqrt(maxHeightNacelles * maxWidthNacelles);
FF = 1 + (0.35 / f_Nacelles);
// Store components
- CDvisc_Nacelles = theAircraftComponents.myNacelles.size() * Cf * FF * QC_Nacelles * Swet_Nacelles / (Sref_Wing + Sref_BackWing);
+ CDvisc_Nacelles = theAircraftComponents.myNacelles.size() * Cf * FF * QC_Nacelles * Swet_Nacelles / (Sref_FrontWing + Sref_BackWing);
return CDvisc_Nacelles;
}
@@ -402,7 +402,7 @@ double viscDragForTandem::calculateViscDragMisc(const Polar& aPolar) {
myRuntimeInfo->debug << " - Get viscous drag Miscellaneous ..." << endl;
double CDvisc_misc = 0.0;
if (calculateFuselage) {
- CDvisc_misc = 3.83 * pow(fuselageUpsweepAngle, 2.5) * (PI * 0.5 * maxWidthFuselage * 0.5 * maxHeightFuselage) / (Sref_Wing + Sref_BackWing);
+ CDvisc_misc = 3.83 * pow(fuselageUpsweepAngle, 2.5) * (PI * 0.5 * maxWidthFuselage * 0.5 * maxHeightFuselage) / (Sref_FrontWing + Sref_BackWing);
}
return CDvisc_misc;
}
diff --git a/aerodynamic_analysis/src/methods/viscDragForTandem.h b/aerodynamic_analysis/src/methods/viscDragForTandem.h
index 428701de37dd6da7fdae3815939898e09015992c..361cbc4cfa72d66413141b61adda93543ff30f87 100644
--- a/aerodynamic_analysis/src/methods/viscDragForTandem.h
+++ b/aerodynamic_analysis/src/methods/viscDragForTandem.h
@@ -31,7 +31,7 @@
class viscDragForTandemInitialization {
public:
// geometry switches
- bool calculateWing; /**< calculate viscous drag of the wing switch */
+ bool calculateFrontWing; /**< calculate viscous drag of the wing switch */
bool calculateFuselage; /**< calculate viscous drag of the fuselage switch */
bool calculateVTP; /**< calculate viscous drag of the VTP switch */
bool calculateBackWing; /**< calcualte viscous drag of the BackWing switch */
@@ -39,7 +39,7 @@ class viscDragForTandemInitialization {
bool calculateMisc; /**< calculate miscellaneous drag switch */
// transition parameters
bool manualTransitionLocation; /**< switch wether transition location is given manually or flow is considered turbulent over all surfaces */
- double transitionLocationWing; /**< relative chord position on wing, where the flow goes from laminar to turbulent [-] */
+ double transitionLocationFrontWing; /**< relative chord position on wing, where the flow goes from laminar to turbulent [-] */
double transitionLocationBackWing; /**< relative chord position on BackWing, where the flow goes from laminar to turbulent [-] */
double transitionLocationVTP; /**< relative chord position on VTP, where the flow goes from laminar to turbulent [-] */
// calibration parameters
@@ -53,7 +53,7 @@ class viscDragForTandemInitialization {
// other
bool jetEngine; /**< switch if aircraft flies with jet engines or propellers */
// geometry
- geom2::MultisectionSurface<geom2::AirfoilSection> theWing; /**< geometry of the main wing */
+ geom2::MultisectionSurface<geom2::AirfoilSection> theFrontWing; /**< geometry of the main wing */
geom2::MultisectionSurface<geom2::AirfoilSection> theBackWing; /**< geometry of the horzontal tail plane */
geom2::MultisectionSurface<geom2::AirfoilSection> theVTP; /**< geometry of the vertical tail plaine */
geom2::MultisectionSurface<geom2::PolygonSection> theFuselage; /**< geometry of the fuselage */
@@ -68,7 +68,7 @@ class viscDragForTandem {
std::filesystem::path aircraftPath;
std::string airfoilPath;
// geometry switches
- bool calculateWing; /**< calculate viscous drag of the wing switch */
+ bool calculateFrontWing; /**< calculate viscous drag of the wing switch */
bool calculateFuselage; /**< calculate viscous drag of the fuselage switch */
bool calculateVTP; /**< calculate viscous drag of the VTP switch */
bool calculateBackWing; /**< calcualte viscous drag of the BackWing switch */
@@ -76,7 +76,7 @@ class viscDragForTandem {
bool calculateMisc; /**< calculate miscellaneous drag switch */
// transition parameters
bool manualTransitionLocation;
- double transitionLocationWing; /**< relative chord position on wing, where the flow goes from laminar to turbulent [-] */
+ double transitionLocationFrontWing; /**< relative chord position on wing, where the flow goes from laminar to turbulent [-] */
double transitionLocationBackWing; /**< relative chord position on BackWing, where the flow goes from laminar to turbulent [-] */
double transitionLocationVTP; /**< relative chord position on VTP, where the flow goes from laminar to turbulent [-] */
// calibration parameters
@@ -91,7 +91,7 @@ class viscDragForTandem {
bool jetEngine; /**< switch if aircraft flies with jet engines or propellers */
// geometry
struct aircraftComponents { /**< struct which stores all possible aircraft geometry elements */
- geom2::MultisectionSurface<geom2::AirfoilSection> myWing; /**< geometry of the main wing */
+ geom2::MultisectionSurface<geom2::AirfoilSection> myFrontWing; /**< geometry of the main wing */
geom2::MultisectionSurface<geom2::AirfoilSection> myBackWing; /**< geometry of the horzontal tail plane */
geom2::MultisectionSurface<geom2::AirfoilSection> myVTP; /**< geometry of the vertical tail plaine */
geom2::MultisectionSurface<geom2::PolygonSection> myFuselage; /**< geometry of the fuselage */
@@ -99,14 +99,14 @@ class viscDragForTandem {
};
aircraftComponents theAircraftComponents;
// geometry dependent wing parameters
- double Sref_Wing; /**< Reference area of the wing [m^2] */
- double Swet_Wing; /**< Wetted area of the wing [m^2] */
- double MAC_Wing; /**< Mean aerodynamic chord of the wing [m] */
- double avgTtoC_Wing; /**< Average thickness to chord ratio of the wing [-] */
- double eta_ref_Wing; /**< Relative span position used for local sweep [-] */
- double phiAtmXtoC_Wing; /**< Local sweep at reference position [rad] */
- double mXtoC_Wing; /**< Chordwise location of airfoil maximum thickness point [-] */
- double QC_Wing; /**< Form factor wing [-] */
+ double Sref_FrontWing; /**< Reference area of the wing [m^2] */
+ double Swet_FrontWing; /**< Wetted area of the wing [m^2] */
+ double MAC_FrontWing; /**< Mean aerodynamic chord of the wing [m] */
+ double avgTtoC_FrontWing; /**< Average thickness to chord ratio of the wing [-] */
+ double eta_ref_FrontWing; /**< Relative span position used for local sweep [-] */
+ double phiAtmXtoC_FrontWing; /**< Local sweep at reference position [rad] */
+ double mXtoC_FrontWing; /**< Chordwise location of airfoil maximum thickness point [-] */
+ double QC_FrontWing; /**< Form factor wing [-] */
// geometry dependent BackWing parameters
double Sref_BackWing; /**< Reference area of the back wing [m^2] */
double Swet_BackWing; /**< Wetted area of the BackWing [m^2] */ //TODO kayra: buradaki parametreleri de degistirmem lazim mi?
@@ -143,11 +143,11 @@ class viscDragForTandem {
// calculations
/** \brief Overall function to calculate viscous drag
* \param aPolar polar/flight condition for which the drag gets calculated
- * \param transitionLocationWing relative transition location where the flow turns turbulent on the wing
+ * \param transitionLocationFrontWing relative transition location where the flow turns turbulent on the wing
* \param transitionLocationBackWing relative transition location where the flow turns turbulent on the BackWing
* \param transitionLocationVTP relative transition location where the flow turns turbulent on the VTP
*/
- std::vector <double> calculateViscDrag(const Polar& aPolar, const double transitionLocationWing,
+ std::vector <double> calculateViscDrag(const Polar& aPolar, const double transitionLocationFrontWing,
const double transitionLocationBackWing, const double transitionLocationVTP);
/** \brief Overall function to calculate viscous drag corrections
* \param componentDrags vector of the component drags which need to be corrected
@@ -157,9 +157,9 @@ class viscDragForTandem {
std::vector <double> calculateCorrectedViscDrag(const std::vector <double>& componentDrags, const double aMachNumber, const double CL);
/** \brief Function to calculate the wing component drag
* \param aPolar polar/flight condition for which the drag gets calculated
- * \param transitionLocationWing relative transition location where the flow turns turbulent on the wing
+ * \param transitionLocationFrontWing relative transition location where the flow turns turbulent on the wing
*/
- double calculateViscDragWing(const Polar& aPolar, const double transitionLocationWing);
+ double calculateViscDragFrontWing(const Polar& aPolar, const double transitionLocationFrontWing);
/** \brief Function to calculate the BackWing component drag
* \param aPolar polar/flight condition for which the drag gets calculated
* \param transitionLocationBackWing relative transition location where the flow turns turbulent on the BackWing
diff --git a/aerodynamic_analysis/src/tandem/tandemCalculatePolarConfig.cpp b/aerodynamic_analysis/src/tandem/tandemCalculatePolarConfig.cpp
index b64f1d82d22562df13618198d9381592fa75e9fe..3c4223d08e4d2468ffa54a6f941497f8575739e2 100644
--- a/aerodynamic_analysis/src/tandem/tandemCalculatePolarConfig.cpp
+++ b/aerodynamic_analysis/src/tandem/tandemCalculatePolarConfig.cpp
@@ -60,7 +60,7 @@ tandemCalculatePolarConfig::tandemCalculatePolarConfig(const node& config)
factorIndDragCleanPolar(EndnodeReadOnly<double>("LiftingLineForTAW/InducedDragCorrection/factorIndDragCleanPolar")),
// visc drag raymer transition parameters
manualTransition(EndnodeReadOnly<bool>("program_settings/ViscDragRaymer/ManualTransition")),
- manualTransitionWing(EndnodeReadOnly<double>("program_settings/ViscDragRaymer/TransitionLocationWing")),
+ manualTransitionFrontWing(EndnodeReadOnly<double>("program_settings/ViscDragRaymer/TransitionLocationWing")),
manualTransitionBackWing(EndnodeReadOnly<double>("program_settings/ViscDragRaymer/TransitionLocationStabilizer")), //TODO kayra:bunu stab mi wing mi yapayim sor
manualTransitionFin(EndnodeReadOnly<double>("program_settings/ViscDragRaymer/TransitionLocationFin")),
// visc drag raymer calibration parameters
@@ -104,7 +104,7 @@ tandemCalculatePolarConfig::tandemCalculatePolarConfig(const node& config)
numberFlightConditions.read(config);
pathToLiftingLine.read(config);
manualTransition.read(config);
- manualTransitionWing.read(config);
+ manualTransitionFrontWing.read(config);
manualTransitionBackWing.read(config);
manualTransitionFin.read(config);
doViscDragCalibration.read(config);
diff --git a/aerodynamic_analysis/src/tandem/tandemCalculatePolarConfig.h b/aerodynamic_analysis/src/tandem/tandemCalculatePolarConfig.h
index ed64e8ed0c2fb3fffb75ea4eb2353180f2129be7..db1b7fe5a229fddd56163a28a057322156242e4e 100644
--- a/aerodynamic_analysis/src/tandem/tandemCalculatePolarConfig.h
+++ b/aerodynamic_analysis/src/tandem/tandemCalculatePolarConfig.h
@@ -55,7 +55,7 @@ class tandemCalculatePolarConfig{
EndnodeReadOnly<double> factorIndDragCleanPolar;
// visc drag raymer
EndnodeReadOnly<bool> manualTransition;
- EndnodeReadOnly<double> manualTransitionWing;
+ EndnodeReadOnly<double> manualTransitionFrontWing;
EndnodeReadOnly<double> manualTransitionBackWing;
EndnodeReadOnly<double> manualTransitionFin;
EndnodeReadOnly<bool> doViscDragCalibration;
diff --git a/aerodynamic_analysis/src/tandem/tandemDefaultStrategy.cpp b/aerodynamic_analysis/src/tandem/tandemDefaultStrategy.cpp
index f1ea09e49fe9d601db4f1df485ff7c3413af407f..9969c097916d9449a13a11d85567b396f3c0e882 100644
--- a/aerodynamic_analysis/src/tandem/tandemDefaultStrategy.cpp
+++ b/aerodynamic_analysis/src/tandem/tandemDefaultStrategy.cpp
@@ -228,8 +228,8 @@ void tandemDefaultStrategy::initializeLiLiforTandem(LiLiforTandemInitialization
void tandemDefaultStrategy::initializeViscDragForTandem(viscDragForTandemInitialization *myViscDragInit) {
// copy geometry
- myViscDragInit->theWing = liftingSurfaces.at(0);
- myViscDragInit->calculateWing = true;
+ myViscDragInit->theFrontWing = liftingSurfaces.at(0);
+ myViscDragInit->calculateFrontWing = true;
myViscDragInit->theBackWing = liftingSurfaces.at(1);
myViscDragInit->calculateBackWing = true;
myViscDragInit->theVTP = VTP;
@@ -241,7 +241,7 @@ void tandemDefaultStrategy::initializeViscDragForTandem(viscDragForTandemInitial
myViscDragInit->calculateMisc = true;
// initialize transition parameters
myViscDragInit->manualTransitionLocation = config_->manualTransition.value(); //TODO kayra: sadece front winge
- myViscDragInit->transitionLocationWing = config_->manualTransitionWing.value();
+ myViscDragInit->transitionLocationFrontWing = config_->manualTransitionFrontWing.value();
myViscDragInit->transitionLocationBackWing = config_->manualTransitionBackWing.value();
myViscDragInit->transitionLocationVTP = config_->manualTransitionFin.value();
// initialize calibration parameters
@@ -323,7 +323,7 @@ void tandemDefaultStrategy::calculateViscDragForTandem(viscDragForTandem *myVisc
// loop over all points to calculate CL dependent visc drag correction hepsini transloc sifir konulmus
for (size_t pointID(0); pointID < currentPolarSet.cleanPolars.at(polarID).Points.size(); ++pointID) {
vector <double> theCorrectedComponentDrags = myViscDragForTandem->calculateCorrectedViscDrag(theComponentDrags, currentPolarSet.cleanPolars.at(polarID).MachNumber,
- currentPolarSet.cleanPolars.at(polarID).Points.at(pointID).CL);
+ currentPolarSet.cleanPolars.at(polarID).Points.at(pointID).CL); //TODO kayra: yine tüm Cl kullaniyor sanirim
// assign total and componentwise viscous drag to the polar map
currentPolarSet.cleanPolars.at(polarID).Points.at(pointID).CD_visc = std::accumulate(theCorrectedComponentDrags.begin(), theCorrectedComponentDrags.end(), 0.0);
currentPolarSet.cleanPolars.at(polarID).PointsFrontWing.at(pointID).CD_visc = theCorrectedComponentDrags.at(0);
@@ -338,6 +338,9 @@ void tandemDefaultStrategy::calculateViscDragForTandem(viscDragForTandem *myVisc
}
void tandemDefaultStrategy::calculateWaveDragMason(waveDragMason *myWaveDragMason) {
+ double frontWingArea = geom2::measure::reference_area(liftingSurfaces.at(0));
+ double backWingArea = geom2::measure::reference_area(liftingSurfaces.at(1));
+ double totalWingArea = frontWingArea + backWingArea;
// run wave drag calculation by Mason over the current polar set
for (size_t polarID(0); polarID < currentPolarSet.cleanPolars.size(); ++polarID) {
double sweepPosition(0.0);
@@ -351,20 +354,20 @@ void tandemDefaultStrategy::calculateWaveDragMason(waveDragMason *myWaveDragMaso
= myWaveDragMason->calculateWaveDrag(currentPolarSet.cleanPolars.at(polarID).Points.at(pointID),
currentPolarSet.cleanPolars.at(polarID).MachNumber,
0, sweepPosition, currentPolarSet.cleanPolars.at(polarID).PointsFrontWing.at(pointID).yStations,
- currentPolarSet.cleanPolars.at(polarID).PointsFrontWing.at(pointID).Cl_distr, false); //TODO kayra: false yaptim cünkü sanirim
- currentPolarSet.cleanPolars.at(polarID).PointsBackWing.at(pointID).CD_wave //tüm lifte bakiyor sikinti cikmasin diye
+ currentPolarSet.cleanPolars.at(polarID).PointsFrontWing.at(pointID).Cl_distr, false) * (frontWingArea / totalWingArea); //TODO kayra: false yaptim cünkü sanirim
+ currentPolarSet.cleanPolars.at(polarID).PointsBackWing.at(pointID).CD_wave //tüm lifte bakiyor sikinti cikmasin diye
= myWaveDragMason->calculateWaveDrag(currentPolarSet.cleanPolars.at(polarID).Points.at(pointID),
currentPolarSet.cleanPolars.at(polarID).MachNumber,
1, sweepPosition, currentPolarSet.cleanPolars.at(polarID).PointsBackWing.at(pointID).yStations,
- currentPolarSet.cleanPolars.at(polarID).PointsBackWing.at(pointID).Cl_distr, false);
- currentPolarSet.cleanPolars.at(polarID).Points.at(pointID).CD_wave = currentPolarSet.cleanPolars.at(polarID).PointsFrontWing.at(pointID).CD_wave // TODO kayra: bunlari toplamak sacma degil mi
+ currentPolarSet.cleanPolars.at(polarID).PointsBackWing.at(pointID).Cl_distr, false) * (backWingArea / totalWingArea);
+ currentPolarSet.cleanPolars.at(polarID).Points.at(pointID).CD_wave = currentPolarSet.cleanPolars.at(polarID).PointsFrontWing.at(pointID).CD_wave
+ currentPolarSet.cleanPolars.at(polarID).PointsBackWing.at(pointID).CD_wave;
}
}
myRuntimeInfo->out << "... Wave drag has been calculated sucessfully!" << endl;
}
-void tandemDefaultStrategy::sumUpDragComponents() { //TODO kayra: burda birtek arka kanadin wave dragi kendi alanina referansla böyle bir sikinti var
+void tandemDefaultStrategy::sumUpDragComponents() {
myRuntimeInfo->out << "Sum up drag components" << endl;
for (size_t polarID(0); polarID < currentPolarSet.cleanPolars.size(); ++polarID) {
for (size_t pointID(0); pointID < currentPolarSet.cleanPolars.at(polarID).Points.size(); ++pointID) {