Transitional Shock-Wave/Boundary-Layer Interactions in Intakes at Incidence
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The work here presents an experimental and computational study of a simplified intake bottom lip at incidence. The experiments are carried out in a small-scale blow-down wind tunnel. Computations are carried out in parallel to experiments using an in-house unstructured compressible flow solver. Evaluation of current Reynolds Averaged Navier-Stokes (RANS) methods are conducted and compared to experimental measurements. Qualitative results show good agreement of experiments to the computations, although further analysis is required. Current computational strategies follow a steady, quasi-two-dimensional approach, with fully structured wall-resolved grids.
KeywordsMach Number Tunnel Liner Static Pressure Distribution Supersonic Region Bottom Dead Centre
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