Impact of incident Mach wave on supersonic boundary layer

被引：0
作者：
A. V. Vaganov
Yu. G. Ermolaev
G. L. Kolosov
A. D. Kosinov
A. V. Panina
N. V. Semionov
A. A. Yatskikh
机构：
[1] Central Aerohydrodynamic Institute,
[2] Khristianovich Institute of Theoretical and Applied Mechanics SB RAS,undefined
[3] Novosibirsk State University,undefined
来源：
Thermophysics and Aeromechanics | 2016年 / 23卷
关键词：
supersonic velocities; experimental studies; wind tunnel; flat plate; sharp and blunt leading edges; boundary layer; hot-wire anemometry;
D O I：
暂无
中图分类号：
学科分类号：
摘要：
Results of an experimental study of the excitation of high-intensity disturbances by a weak external shock wave in laminar boundary layer on flat-plate models with sharp and blunted leading edges at М = 2.5 are reported. The field of disturbances produced by a 2D sticker in turbulent boundary layer on the wall of wind-tunnel test section in the free stream is shown to have the form of an N-wave. It is found that, on the blunted plate, the intensity of pulsations produced by weak external shock waves in boundary layer several times exceeds the intensity of pulsations produced in boundary layer on the model with a sharp leading edge.
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页码：43 / 48
页数：5
相关论文
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