Use of vortex generators to control internal supersonic flow separation

被引：5
|
作者：
Szumowski, A [1 ]
Wojciechowski, J [1 ]
机构：
[1] Warsaw Univ Technol, Inst Aeronaut & Appl Mech, PL-00665 Warsaw, Poland
来源：
AIAA JOURNAL | 2005年 / 43卷 / 01期
关键词：
D O I：
10.2514/1.5741
中图分类号：
V [航空、航天];
学科分类号：
08 ; 0825 ;
摘要：
The capability of various boundary-layer manipulations to delay separation in a supersonic internal flow was investigated. An asymmetric two-dimensional convergent-divergent channel with a planar surface at one side and a bump having a cylindrical contour with a diameter of 500 mm was used. The experiments were conducted in the transonic wind tunnel discharging into a downstream container evacuated before the test. The normalized pressure distributions along the nozzle surface were shown for four settings of the adjusting valve of the tunnel.
引用
收藏
页码：216 / 218
页数：3
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