To the Theory of Hypersonic Flow around a Thin Delta Finite-Swept Wing at a Large Attack Angle

被引：0
|
作者：
Golubkin, V. N. [1 ]
机构：
[1] Zhukovsky Cent Aerohydrodynam Inst, Zhukovskii 140181, Moscow Region, Russia
来源：
FLUID DYNAMICS | 2020年 / 55卷 / 07期
关键词：
hypersonic flow; delta wing; thin shock-layer method; classification of flow regimes; entropy layer; composite solution;
D O I：
10.1134/S0015462820070058
中图分类号：
O3 [力学];
学科分类号：
08 ; 0801 ;
摘要：
The paper reviews the most important results in solving the problem of a hypersonic flow around a thin finite-swept delta wing at large angles of attack close to the right angle obtained by the author using the thin shock-layer method. The classification of all the basic modes and schemes of the flows realized in the proposed theory is supplemented by the two main similarity parameters. A composite solution, which adequately represents the disturbed flow both in the main shock-layer part and in the near-wall entropy layer, is obtained.
引用
收藏
页码：904 / 914
页数：11
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