Evaluation of Explicit Algebraic Reynolds-Stress Models for Separated Supersonic Flows

High-Reynolds-number supersonic e owe elds were generated numerically to assess the performance of three explicit algebraic Reynolds-stress turbulence models. The cone gurations consist of a shock/boundary-layer interaction and a 24-deg compression ramp, both of which exhibit an appreciable region of separated e ow. Solutions were also obtained using standard zero-equation and k‐ models. Details of the computations are summarized, and the accuracy of numerical results is established via grid resolution studies. Comparisons are made with experimental data in terms of surface pressure and skin friction, as well as off-surface proe les of mean velocity and componentsoftheReynolds-stresstensor. Forthee owsconsidered here, it isfound that thealgebraic-stressmodels offer little improvement over existing closures.