Effect of the cone nose bluntness and the ultrasonically absorptive coating on transition in a hypersonic boundary layer

DOI10.1134/S0015462810060074zbMath1233.76006OpenAlexW2023399899MaRDI QIDQ665591

A. N. Shiplyuk, D. A. Buntin, S. V. Lukashevich, Anatoly A. Maslov

Publication date: 5 March 2012

Published in: Fluid Dynamics (Search for Journal in Brave)

Full work available at URL: https://doi.org/10.1134/s0015462810060074

zbMATH Keywords

laminar-turbulent transitionbluntnesshypersonic boundary layersecond-mode disturbancesultrasonically-absorptive coating

Mathematics Subject Classification ID

Experimental work for problems pertaining to fluid mechanics (76-05) Hypersonic flows (76K05) Boundary-layer theory for compressible fluids and gas dynamics (76N20)

Cites Work

• Stabilization of a hypersonic boundary layer using an ultrasonically absorptive coating

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