Numerical Investigations of Effusion Cooling in Hypersonic Boundary-Layer Flow
نویسندگان
چکیده
Direct numerical simulations (DNS) are carried out to investigate the effect of effu-sion cooling by blowing through spanwise slits and discrete holes in a laminar flat-plate boundary layer at various Mach numbers. The comparison with experimental data for a Mach-2.67 boundary layer with a cool wall and a spanwise slit shows good agreement. For an adiabatic Mach-6 boundary layer, the focus of the study is the effectiveness of various effusion-cooling configurations (slits and holes), the generated vortices and shear-layer systems. In terms of cooling effectiveness slits are preferable over (a few) holes.
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