Reynolds stress modeling for hypersonic flows

Despite the enormous increase in computational capabilities and use of computational fluid dynamics as a design tool in the aircraft industry, the correct prediction of complex hypersonic turbulent flows involving shock wave boundary layer interaction (SWBLI) is still a challenge [1]. Well assessed turbulence models that are known to perform properly at lower speed, cannot be used in hypervelocity flows without a proper validation. In this paper the use of a differential Reynolds Stress Model for the prediction of SWBLI on a compression corner is presented and the results are discussed for attached and separated boundary layers