Обтекание моделей гиперзвуковых летательных аппаратов и простых геометрических форм в гиперзвуковой ударной аэродинамической трубе

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М.А. Котов, И.А. Крюков, Л.Б. Рулева, С.И. Солодовников, С.Т. Суржиков
8 Инженерный журнал: наука и инновации # 9·2016
Flow around hypersonic aircraft models
and simple geometries in a hypersonic shock tunnel
© M.A. Kotov, I.A. Kryukov, L.B. Ruleva,
S.I. Solodovnikov, S.T. Surzhikov
Ishlinsky Institute for Problems in Mechanics RAS, Moscow, 119526, Russia
We studied shockwave configurations obtained during hypersonic gas flow around frag-
ments 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.
Keywords: hypersonic flow, hypersonic aerodynamics, shock tunnel.
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Kotov M.A. , Cand. Sci. (Phys.-Math.), Researcher, Ishlinsky Institute for Problems in
Mechanics RAS. Author of 18 publications in the field of aerothermophysiks. e-mail: