High-pressure layer generation in a compression corner at a supersonic flow velocity

被引：5
|
作者：
Zapryagaev, V. I. [1 ]
Kavun, I. N. [1 ]
Lipatov, I. I. [2 ]
机构：
[1] Khristianovich Inst Theoret & Appl Mech, Novosibirsk 630090, Russia
[2] Cent Aerohydrodynam Inst TsAGI, Zhukovskii 140180, Moscow Oblast, Russia
来源：
FLUID DYNAMICS | 2014年 / 49卷 / 06期
基金：
俄罗斯基础研究基金会;
关键词：
supersonic flow; separation; shock waves; compression corner;
D O I：
10.1134/S0015462814060131
中图分类号：
O3 [力学];
学科分类号：
08 ; 0801 ;
摘要：
The results of an experimental and numerical investigation of a three-dimensional laminar separated flow in a compression corner are presented. The freestream Mach number M-a =6. The model under study is a plate with a sharp leading edge on which a step with a 30A degrees inclination angle is mounted. The model width is equal to the plate length from the leading edge to the step. A thin high-pressure layer located above the boundary layer, downstream of the reattachment line is shown to exist.
引用
收藏
页码：819 / 826
页数：8
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