Dynamic layer formation in the reattachment zone for a supersonic laminar separated flow

被引：1
|
作者：
Zapryagaev, Valeriy, I [1 ]
Kavun, Ivan N. [1 ]
Trubitsyna, Lukeriya P. [1 ]
机构：
[1] Russian Acad Sci, Khristianovich Inst Theoret & Appl Mech, Siberian Branch, Novosibirsk 630090, Russia
来源：
PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART G-JOURNAL OF AEROSPACE ENGINEERING | 2022年 / 236卷 / 03期
关键词：
Boundary layer; compression corner; separation flow; shock wave; supersonic flow;
D O I：
10.1177/0954410018809600
中图分类号：
V [航空、航天];
学科分类号：
08 ; 0825 ;
摘要：
In this work, results of an experimental study of the flow structure in the region of reattachment of a supersonic laminar separated flow are reported. The separated flow is generated by a model shaped as a compression corner consisting of a horizontal flat plate followed by a ramp. The model width is equal to the plate length from the leading edge to the plate/ramp junction line. The ramp angle is varied in the interval phi = 20 degrees-50 degrees. The free-stream Mach number is M-infinity = 6 or 8. The analysis of the Pitot pressure profiles near the ramp wall in the downstream direction behind the reattachment line confirms the existence of a high-pressure layer with the total pressure being appreciably greater than in the surrounding flow.
引用
收藏
页码：477 / 489
页数：13
相关论文
共 50 条
12345