Aggiunto file coefficientToCsv

utilities/coefficientToCvs.m

+close; clear; clc;
+
+%% Imposta il razzo e importa i coefficienti aerodinamici
+r = Rocket(Mission(true));
+coefficient = r.coefficients;
+
+
+% Dati geometrici fissi
+airbrakeI = 1;       % [-]
+xcgI      = 1;       % [m]
+lRef      = (coefficient.geometry.chord1 + coefficient.geometry.chord2) / 2; % Corda media [m]
+P = [0 1 0;
+     0 0 -1;
+    -1 0 0];
+
+% Preallocazione lunghezze
+numAlphas    = length(coefficient.state.alphas);
+numMachs     = length(coefficient.state.machs);
+numBetas     = length(coefficient.state.betas);
+numAltitudes = length(coefficient.state.altitudes);
+
+N = numAlphas * numMachs * numBetas * numAltitudes;  % 45980
+
+% Preallocazione tabelle per salvare i risultati: [alpha, beta, mach, Re, coefficiente]
+dataCQ = zeros(N, 5);
+dataCL = zeros(N, 5);
+dataCD = zeros(N, 5);
+dataCm = zeros(N, 5);
+dataCn = zeros(N, 5);
+dataCr = zeros(N, 5);
+
+% Ciclo annidato su tutti gli stati aerodinamici
+idx = 1;
+tic; 
+for i = 1 : numAlphas
+    alpha = coefficient.state.alphas(i) * pi/180; % [rad]
+    M1 = [ 1    0           0;
+           0 cos(alpha)  sin(alpha);
+           0 -sin(alpha) cos(alpha)];
+
+    for j = 1 : numMachs
+            mach  = coefficient.state.machs(j);           % [-]
+
+        for k = 1 : numBetas
+            beta  = coefficient.state.betas(k) * pi/180;  % [rad]
+            M2 = [cos(beta) 0 sin(beta);
+                     0      1      0;
+                -sin(beta)  0  cos(beta)];
+
+            for h = 1 : numAltitudes
+                alt   = coefficient.state.altitudes(h);       % [m]
+ 
+                % Estrae i coefficienti aerodinamici in quella configurazione
+                coefficientForce = coefficient.static(1:3, i, j, k, h, airbrakeI, xcgI);
+                coefficientMoment = coefficient.static(4:6, i, j, k, h, airbrakeI, xcgI);
+               
+
+                % Forze trasformate nel sistema corpo
+                L = ((M1*M2)\eye(3)) * P * coefficientForce;
+                L([2,3]) = - L([2,3]);
+
+                % Momenti trasformati nel sistema corpo
+                M = ((M1*M2)\eye(3))*P*coefficientMoment;
+                M([2,3]) = - M([2,3]);
+
+
+                % Coefficenti finali 
+                cQ = L(1); % Side force coefficient
+                cL = L(2); % Lift coefficient
+                cD = L(3); % Drag coefficient
+                cm = M(1); % Pitching moment coefficient
+                cn = M(2); % Yawing moment coefficient
+                cr = M(3); % Rolling moment coefficient
+
+                % Calcolo Reynolds
+                [~, a, ~, ~, nu, ~] = atmosisa(alt);
+                Re = (mach * a * lRef) / nu;
+
+                % Salvataggio righe nei dataset
+                dataCQ(idx,:) = [alpha, beta, mach, Re, cQ];
+                dataCL(idx,:) = [alpha, beta, mach, Re, cL];
+                dataCD(idx,:) = [alpha, beta, mach, Re, cD];
+                dataCm(idx,:) = [alpha, beta, mach, Re, cm];
+                dataCn(idx,:) = [alpha, beta, mach, Re, cn];
+                dataCr(idx,:) = [alpha, beta, mach, Re, cr];
+
+                idx = idx + 1;
+            end
+        end
+    end
+end
+tempoCicloFor = toc;
+
+% Esportazione su file CSV 
+filenames = {'cQ.csv', 'cL.csv', 'cD.csv', 'cm.csv', 'cn.csv', 'cr.csv'}; % ATTENZIONE cr andrà rinominata manualmente in cl affinchè sia accettata da RocketPy
+datasets  = {dataCQ,  dataCL,  dataCD,  dataCm,  dataCn,  dataCr};
+header = {'alpha', 'beta', 'mach', 'Reynolds', 'coefficient'};
+
+for idx = 1:numel(filenames)
+    T = array2table(datasets{idx}, 'VariableNames', header);
+    writetable(T, filenames{idx});
+end