Edited thrust correction equation

Code/MAD_H300/MAD_H300.m

@@ -1,7 +1,7 @@
 clc
 addpath('../')
 
-mad_H300 = SingleStageRocket(0.31, 5.712, 1, 148, 158, 15.77, 0.0283);
+mad_H300 = SingleStageRocket(0.31, 5.712, 10, 148, 158, 15.77, 0.028353);
 mad_H300.SetSimulationParams(0.05, 20000, 85);
 mad_H300.SetRocketID("MAD_H300");
 mad_H300.InitializeVars();

Code/SingleStageRocket.m

@@ -178,7 +178,7 @@ classdef SingleStageRocket < handle
        
        function T = VacThrustCorrection(obj, h, thrust)
            [t,p,rho] = CalcAtmosQuantities(h);
-           T = thrust - 0;
+           T = thrust - obj.exit_area * p;
        end
        
        % Calculate mass at each iteration
@@ -383,7 +383,8 @@ classdef SingleStageRocket < handle
                text = "VariableMassFlow";
                result_dat_file = 'Result/' + obj.ID + "_Result_" + obj.launch_angle + "_deg_" + text + ".txt";
            end
-           result_matrix = [obj.t obj.x/1000 obj.y/1000 obj.V obj.M obj.thrust obj.DvDt obj.m obj.mdot obj.isp obj.Cd obj.q];
+           result_matrix = [obj.t(1:obj.NStepEnd) obj.x(1:obj.NStepEnd)/1000 obj.y(1:obj.NStepEnd)/1000 obj.V(1:obj.NStepEnd) obj.M(1:obj.NStepEnd) obj.thrust(1:obj.NStepEnd) ...
+               obj.DvDt(1:obj.NStepEnd) obj.m(1:obj.NStepEnd) obj.mdot(1:obj.NStepEnd) obj.isp(1:obj.NStepEnd) obj.Cd(1:obj.NStepEnd) obj.q(1:obj.NStepEnd)];
            result_data = reshape(result_matrix, [], 12);
            dlmwrite(result_dat_file, 'Time(s),x(km),y(km),Velocity(m/s),Mach,Thrust(N),Acceleration(m/s2),Mass(kg),mdot(kg/s),Isp(s),Cd,DynPres(kPa)','delimiter','')
            dlmwrite(result_dat_file, result_data, '-append', 'delimiter', ',');