Numerical Analysis of Oblique Impinge shock-wave/turbulent boundary-layer interaction Using Reynolds Average Navier Stroke Equations

Abstract

Interaction of shock waves with turbulent boundary layer plays an important role in the design and operability of high-speed aerospace vehicles and air-breathing engines. During interaction, the adverse pressure gradient of the shock is often strong enough to separate the boundary layer. Reynolds averaged Navier-Stokes simulations using conventional turbulence models do not predict the correct size and shape of the separation bubble in strong shock/turbulent boundary-layer interactions. The corresponding surface predictions exhibit large discrepancy with respect to experimental measurements. The inaccuracies are often attributed to the fact that conventional turbulence models do not account for the unsteady effects in shock/turbulent boundary-layer interaction. In this Research paper, the prediction of Reynolds averaged navier stroke equations has been studying numerically over one of the classification of shockwave boundary layer interaction in Two-dimensional oblique impingement configuration. Linear Eddy Viscosity models and their effects over hypersonic configuration and noticed variations using several equation tools i.e. one equal model, two equation model and so forth .Presence of multiple shockwaves, adverse pressure gradient, shock bubble, skin friction and pressure over wall, and flow expansion in the interaction region make it more challenging to implement the shock bubble than earlier compression corner applications. The function used to identify the location and extent of shock waves and shock bubble need to be altered. Also, the variation of flow quantities upstream of the different shock-waves cannot be prescribed a priori , as in the compression corner cases. Linear eddy viscosity models are considering manipulating the contours over the entire domain i.e one equation model, two equation models. The current paper addresses these issues are detail and present an improved implementation of the shock-unsteadiness modification for practical flows. Keywords : High-speed flows, shock wave, turbulent boundary layer, separation bubble, turbulence Modeling, hypersonic, single-fin, scramjet inlet, cone-flare