Experimental study of stability of supersonic boundary layer on swept wing

被引：0
|
作者：
Semionov, N. V. [1 ]
Kosinov, A. D. [1 ]
Yermolaev, Yu. G. [2 ]
机构：
[1] Inst Theoret & Appl Mech, Inst Skaya 4-1, Novosibirsk 630090, Russia
[2] Khristianovitch Inst, Theoret & Appl Mech, Novosibirsk 630090, Russia
来源：
SEVENTH IUTAM SYMPOSIUM ON LAMINAR-TURBULENT TRANSITION | 2010年 / 18卷
关键词：
D O I：
10.1007/978-90-481-3723-7_61
中图分类号：
TH [机械、仪表工业];
学科分类号：
0802 ;
摘要：
The paper is devoted to an experimental study of laminar-turbulent transition and instability disturbances evolution in a three-dimensional supersonic boundary layer on swept wing with sharp leading edge. The detailed data of natural disturbances development are obtained for the first time Characteristic zones of disturbances evolution are determined. A position of instability region of secondary flow is experimentally defined Some features of disturbances evolution, characteristic only for a supersonic boundary layer are revealed It was shown experimentally that secondary cross-flow instability plays the main role in laminar-turbulent transition in 3-D supersonic boundary layers.
引用
收藏
页码：379 / +
页数：2
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