On the Oblique Breakdown Mechanism in a Supersonic Boundary Layer on a Swept Wing at Mach 2

被引：1
|
作者：
Panina, A. V. [1 ]
Kosinov, A. D. [1 ,2 ]
Semionov, N. V. [1 ]
Yermolaev, Yu. G. [1 ]
机构：
[1] Khristianovich Inst Theoret & Appl Mech, Inst Skaya 4-1, Novosibirsk 630090, Russia
[2] Novosibirsk State Univ, Pirogova 2, Novosibirsk 630090, Russia
来源：
PROCEEDINGS OF THE XXV CONFERENCE ON HIGH-ENERGY PROCESSES IN CONDENSED MATTER (HEPCM 2017) | 2017年 / 1893卷
关键词：
STABILITY; TRANSITION; WAVE;
D O I：
10.1063/1.5007538
中图分类号：
O59 [应用物理学];
学科分类号：
摘要：
The results of an experimental study of the controlled pulsations development in the spanwise modulated boundary layer of a swept wing are presented in the paper. The experiments were conducted at Mach 2 and unit Reynolds number Re-1 = 6x10(6) m(-1). The square stickers were applied to induce the spanwise modulation of mean flow in the boundary layer. It was obtained, that the presence of roughness leads to a decrease of the disturbance source efficiency at the subharmonic and fundamental frequency, and the oblique breakdown mechanism begins to appear at smaller values of the longitudinal coordinate x as compared with the case of a smooth wing.
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页数：5
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