Hypersonic Shock-Wave/Boundary Layer Interactions with an Implicit Navier-Stokes Solver
A fully implicit Navier-Stokes solver is used to calculate two-dimensionnal generic hypersonic geometries. Peak heating and shock wave/boundary layer interaction features are illustrated by computations over compression ramps, (representative of flows over control surfaces), and generic nose-to-canopy flows (double ellipse geometry with zero incident flow). Comparisons with experimental data is commented.
Key wordsBoundary-layer interactions Separation Reattachment Hypersonics
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