V. Borovoy  , V. Mosharov , V. Radchenko , and A. Skuratov

DOI Number XXX-YYY-ZZZ

Conference Number HiSST2018_47801549

An experimental study of the interaction of shock waves near a cylinder perpendicular to a blunted plate was carried out. The experiments were made in the Ludwig wind tunnel at Mach number M∞=5 and different Reynolds numbers Re∞L in the range from 0.6 107 to 4.0 107 . The heat fluxes to the model surface, measured using Temperature Sensitive Paint (TSP), were analyzed. The influence of the plate blunting radius and the distance of cylindrical obstacle from plate leading edge on the gas flow are studied.

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In Categories: High-Speed Aerodynamics and Aerothermodynamics, HiSST 2018, Hypersonic Aerodynamics, Materials and Structures
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