Add aerodynamics

include/Aerodynamics.hpp

@@ -0,0 +1,35 @@
+#pragma once
+#include "IAerodynamics.hpp"
+#include "State.hpp"
+#include <iostream>
+#include <vector>
+#include <string>
+using namespace std;
+
+class DragFromFile : public IAerodynamics {
+private:
+    vector<double> mach;
+    vector<double> cd; 
+    double MaxMach = 0.0; 
+    double MinMach = 0.0; 
+
+    void readTable(const string& filename);
+
+    double interpolateCD(double MachInput) const;
+
+public:
+
+    DragFromFile();
+
+    explicit DragFromFile(const string& filename);
+
+    double GetmaxMach() const;
+
+    double GetminMach() const;
+
+    double GetCd(const State& aerodynamicState) const override;
+
+    double getCdFromMach(double mach) const;
+
+    Eigen::Vector3d GetMomentCoefficients(const State& aerodynamicState) const override;
+};

main.cpp

@@ -1,4 +1,37 @@
+#include "Aerodynamics.hpp"
+#include "State.hpp"
+#include <iostream>
+#include <string>
+#include <iomanip>
+#include <stdexcept>
+using namespace std;
 
 int main() {
+    string input = " ";
+    double MachInput = 0.0;
+
+    DragFromFile aero("cd.csv");
+    double MinMach = aero.GetminMach();
+    double MaxMach = aero.GetmaxMach();
+
+    try{
+        cout << "enter a Mach Number(" << MinMach << "<= M <=" << MaxMach << "): ";
+        getline(cin, input);
+        MachInput = stod(input);
+        if (MachInput < 0.00 || MachInput > 3.00) throw logic_error (" Value of Mach number should be in the range");
+    }
+    catch(const exception& e)
+    {
+        cout << "Error in the input" << e.what() << endl;
+        return 1;
+    }
+
+    State state(1);
+    state[0] = MachInput;
+
+    double cd = aero.GetCd(state);
+
+    cout << fixed << setprecision(5);
+    cout << "Drag coefficient: " << cd << endl;
     return 0;
-}
+}

src/aerodynamics/DragFromFile.cpp

@@ -0,0 +1,98 @@
+#include "Aerodynamics.hpp"
+#include <iostream>
+#include <vector>
+#include <string>
+#include <fstream>
+#include <algorithm>
+#include <stdexcept>
+using namespace std;
+
+DragFromFile::DragFromFile() = default;
+
+DragFromFile::DragFromFile(const string& filename)
+{
+    readTable(filename);
+}
+
+void DragFromFile::readTable(const string& filename)
+{
+    ifstream vMyFile(filename);
+    if (!vMyFile.good())
+    {
+        throw runtime_error("Failed to open file: " + filename);
+        return;
+    }
+
+    mach.clear();
+    cd.clear();
+
+    double Mach_data;
+    double Cd_data;
+    char comma;
+
+    while (vMyFile >> Mach_data >> comma >> Cd_data)
+    {
+        mach.push_back(Mach_data);
+        cd.push_back(Cd_data);
+    }
+
+    auto range = minmax_element(mach.begin(), mach.end());
+    MinMach = *range.first;
+    MaxMach = *range.second;
+    vMyFile.close();
+}
+
+double DragFromFile::interpolateCD(double MachInput) const
+{
+    if (mach.empty()) return 0.0;
+
+    for (size_t i = 0; i < mach.size() - 1; i++)
+    {
+    if (MachInput >= mach[i] && MachInput <= mach[i+1])
+        {
+            return cd[i] + (cd[i+1] - cd[i]) * (MachInput - mach[i]) / (mach[i+1] - mach[i]);
+        }
+    }
+
+    return cd.back();
+}
+
+double DragFromFile::GetmaxMach() const
+{
+    return MaxMach;
+}
+
+
+double DragFromFile::GetminMach() const
+{
+    return MinMach;
+}
+
+double DragFromFile::GetCd(const State& aerodynamicState) const
+{
+    if (aerodynamicState.size() > 0)
+    {
+        double mach = aerodynamicState[0];
+        if (mach >= MinMach && mach <= MaxMach)
+        {
+            return interpolateCD(mach);
+        }
+        else
+        {
+            throw out_of_range("Mach number out of range.");
+        }
+    }
+
+    throw std::invalid_argument("State is empty");
+}
+
+double DragFromFile::getCdFromMach(double mach) const
+{
+    return interpolateCD(mach);
+}
+
+
+Eigen::Vector3d DragFromFile::GetMomentCoefficients(const State&) const
+{
+    return Eigen::Vector3d::Zero();
+}