4TH EUROPEAN CONFERENCE FOR AEROSPACE SCIENCES Large-Eddy Simulation of High Mach Number Film Cooling with Shock-Wave Interaction
نویسندگان
چکیده
The impact of shock waves on supersonic cooling films is studied using large-eddy simulations (LES). A laminar cooling film is injected through a slot at a Mach number Mai = 1.8 into a fully turbulent boundary layer at a freestream Mach number Ma∞ = 2.44. The cooling film is disturbed by oblique shock waves at deflection angles of 5° and 8° at two downstream positions of the slot. At shock impingement close to the slot, i.e., within the potential-core region, at a flow deflection of 5°, a cooling effectiveness decrease of 33 % occurs downstream of the separation bubble compared to a configuration without shock impingement. If the same shock impinges further downstream upon the boundary-layer region, the decrease is only 17 %. The stronger 8° shock wave at the further downstream impingement position leads to a maximum decrease of 33 %.
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