Interaction of shock waves with turbulent boundary layer and laminar boundary layer is investigated. Numerical investigation of gas flow on a flat plate near a single fin and a fin pair, generating crossings shocks, is performed at Mach numbers M_∞ = 5 (Re_(∞L) = 27×10~6) u M_∞ = 6 (Re_(∞L) = 19×10~6). The study is focused upon the plate bluntness influence on the flow field and heat transfer in the interaction region.
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