Abstract
Because of viscous interaction in hypersonic flows, the state of the boundary layer significantly influences possible shock-wave boundary-layer interaction as well as surface heat loads. Hence, for engineering applications, the efficient numerical prediction of the laminar-to-turbulent transition is a challenging and important task. Within the framework of the Reynolds-averaged Navier–Stokes equations, Langtry–Menter proposed the transition model using two transport equations for the intermittency and combined with the shear stress transport turbulence model. The transition model contains two empirical correlations for the onset and length of transition. Langtry–Menter designed and validated the correlations for the subsonic and transonic flow regimes. For applications in the hypersonic flow regime, the development of a new set of correlations proved necessary. Within this paper, we propose a next step and couple the transition model with the Speziale–Sarkar–Gatski/Launder–Reece–Rodi Reynolds stress turbulence model, which we found to be well suited for scramjet intake simulations. First, we illustrate the necessary modifications of the Reynolds stress model and the hypersonic in-house correlations using a hypersonic flat plate test case. Next, the transition model is successfully validated for its use coupled to both turbulence models using a hypersonic double ramp test case. Regardless of the turbulence model, the transition model is able to correctly predict the transition process compared to experimental data. In addition, we apply the transition model combined with both turbulence models to three different fully three-dimensional scramjet intake configurations that are experimentally investigated in wind tunnel facilities. The agreement with the available experimental data is also shown.
Published Version
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