diff --git a/RoccarasoFlight/postprocessing/RPS/dataAnalyzer.m b/RoccarasoFlight/postprocessing/RPS/dataAnalyzer.m
index 081f1fdd1e5451b9665d1ced8464a8e4c3c9ef40..49f6d72be7e681a71d6b9028e05ea7951db7cf84 100644
--- a/RoccarasoFlight/postprocessing/RPS/dataAnalyzer.m
+++ b/RoccarasoFlight/postprocessing/RPS/dataAnalyzer.m
@@ -39,6 +39,11 @@ engineSim = combustionSimulation(engine, settings);
 % Computing actual performances
 engineFly = performanceReconstruction(engine, engineSim);
 
+% Loading MSA simulated motor for the flight
+load("HREmotors.mat");
+engineMSA = HREmotors(59);
+clear HREmotors;
+
 %% PLOTTING
 fprintf('DATA ANALYSIS CONCLUDED: \n\n')
 fprintf('\t - Total Impulse simulated: %.2f\n', engineSim.performances.Itot)
@@ -78,8 +83,9 @@ if settings.plots
     plot(engineSim.time, engineSim.performances.T)
     hold on; grid minor
     plot(engineFly.time, engineFly.T)
+    plot(engineMSA.t, engineMSA.T)
     ylabel('Thrust [N]'); xlabel('Time [s]'); title('Thrust compare')
-    legend('Simulated', 'Computed')
+    legend('Simulated', 'Computed', 'MSA-SFT06')
     axis padded
 end
 
diff --git a/RoccarasoFlight/postprocessing/RPS/msaData/HREmotors.mat b/RoccarasoFlight/postprocessing/RPS/msaData/HREmotors.mat
new file mode 100644
index 0000000000000000000000000000000000000000..b7b3c10914d77aee38c5c66ed75e6f72bdf9926f
Binary files /dev/null and b/RoccarasoFlight/postprocessing/RPS/msaData/HREmotors.mat differ
diff --git a/RoccarasoFlight/postprocessing/RPS/msaEngineData.mat b/RoccarasoFlight/postprocessing/RPS/msaEngineData.mat
index 1603214baff3dd313ed2ff0b4e98cc1f8bbf7a99..0cdec558af9edf9ae92a240128b897ec6ee850c5 100644
Binary files a/RoccarasoFlight/postprocessing/RPS/msaEngineData.mat and b/RoccarasoFlight/postprocessing/RPS/msaEngineData.mat differ
diff --git a/RoccarasoFlight/postprocessing/RPS/src/combustionSimulation.m b/RoccarasoFlight/postprocessing/RPS/src/combustionSimulation.m
index bdacbf726dbde03c0ea8d8ea92a7cf194c9893e7..1bfaeaf8c5f67537f3d6fdc6068dfdb133e9878b 100644
--- a/RoccarasoFlight/postprocessing/RPS/src/combustionSimulation.m
+++ b/RoccarasoFlight/postprocessing/RPS/src/combustionSimulation.m
@@ -59,6 +59,8 @@ g0          = settings.g0;
 %% COMBUSTION SIMULATION
 % Defining the time
 engineSim.time = engine.acquisition.cutData.timePTop - engine.acquisition.cutData.timePTop(1);
+
+% Saving the oxidizer mass flow in the out-struct
 engineSim.mfr.mox = engine.performances.mox;
 
 % Performing Marxman simulation
@@ -83,6 +85,7 @@ OF = engineSim.mfr.mox./engineSim.mfr.mf;
 OF(1) = OF(2);
 engineSim.performances.OF = OF;
 
+% Fixing convergence problems in the first transitory phase (performances are not relevant in this phase)
 ii = find(OF < 2);
 OF(ii) = 2;
 
@@ -114,7 +117,7 @@ end
 Pe = real(Pe');
 
 % Thrust coefficient
-cT = sqrt(2*y.^2./(y - 1).*(2./(y + 1)).^((y + 1)./(y - 1))).*sqrt(1 - (Pe./Pc).^((y - 1)./y)) * lambda + (Pe - Pamb)./Pc.*epsilon;
+cT = sqrt(2*y.^2./(y - 1).*(2./(y + 1)).^((y + 1)./(y - 1))).*sqrt(1 - (Pe./Pc).^((y - 1)./y)) * lambda;
 
 % Thrust
 T  = cT.*Pc*1e5*At*etacT;