In this work we present semi-intrusive and non-intrusive techniques for uncertainties quantification (UQ) in the context of the solution of partial differential equations, with a specific application to aerodynamics problems. These methods has been applied successfully to a supersonic nozzle flow and the analysis of an inviscid transonic flow over a RAE 2822 airfoil. In this case, we consider three uncertainties, on the Mach number, the angle of attack and the heat coefficient ratio and the numerical results are compared with experimental data.