Flow around hypersonic aircraft models and simple geometries in a hypersonic shock tunnel
Published: 13.09.2016
Authors: Kotov M.A., Kryukov I.A., Ruleva L.B., Solodovnikov S.I., Surzhikov S.T.
Published in issue: #9(57)/2016
DOI: 10.18698/2308-6033-2016-9-1537
Category: Aviation and Rocket-Space Engineering | Chapter: Aerodynamics and Heat Transfer Processes in Aircrafts
We studied shockwave configurations obtained during hypersonic gas flow around fragments of hypersonic aircraft. The article describes our test installation. We analyse the experimental data on flows around an acute wedge and a cylinder. These models pose as "simple geometry" models for testing new computation codes. We supply the results of comparing data obtained during computation and experimentation.
References
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