Boundary-layer instability on sharp cone at Mach 3.5 with controlled input

被引：43

作者：

Corke, TC ^{[1
]}

Cavalieri, DA

Matlis, E

机构：

[1] Univ Notre Dame, Ctr Flow Phys & Control, Dept Aerosp Engn & Mech, Notre Dame, IN 46556 USA

[2] IIT, Dept Mech & Aerosp Engn, Chicago, IL 60616 USA

来源：

AIAA JOURNAL | 2002年 / 40卷 / 05期

关键词：

Actuator arrays;

D O I：

10.2514/2.1744

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

An experiment was carried out to introduce pairs of oblique waves in a supersonic boundary layer on a thin cone. The experiment was performed in the 0.5-m Mach 3.5 quite tunnel at NASA Langley Research Center in order to minimize the required levels of controlled disturbances. The experimental results showed the growth of a sub-harmonic disturbance.

引用

页码：1015 / 1018

页数：4

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