PREDICTION OF SUPERSONIC INLET PERFORMANCES WITH 3D NAVIER-STOKES CALCULATIONS

This paper presents a computational methodology developed to predict the performances of supersonic inlets and its validation against well documented experimental data. The forebody computations, the choice of the exit boundary condition and the calculation of the inlet are described. The results of this methodology in terms of computational cost and accuracy of the total pressure recovery and mass flow rate predictions are very satisfactory. Nomenclature