Numerical and experimental investigation of viscous shock layer receptivity and instability

被引：0
|
作者：
Kudryavtsev, A. [1 ]
Mironov, S. [1 ]
Poplavskaya, T. [1 ]
Tsyryulnikov, I. [1 ]
机构：
[1] Russian Acad Sci, Siberian Div, Khristianovich Inst Theoret & Appl Mech, Novosibirsk 630090, Russia
来源：
SHOCK WAVES, VOL 1, PROCEEDINGS | 2009年
关键词：
D O I：
10.1007/978-3-540-85168-4_106
中图分类号：
O64 [物理化学（理论化学）、化学物理学];
学科分类号：
070304 ; 081704 ;
摘要：
A hypersonic viscous shock layer over a flat plate at the free-stream Mach number M-infinity = 21 is investigated both numerically and experimentally. The shock layer is excited by either external acoustic field or blowing/suction on the plate surface. The interaction of disturbances with the leading edge shock wave and their development in the boundary layer are simulated by solving the Navier-Stokes equations with a high-order shock-capturing scheme. Data of numerical simulations axe compared very favorably with measurements conducted in a hypersonic nitrogen wind tunnel using the electron-beam fluorescence techniques. Numerical simulations show that the interference between natural and artificially excited disturbances can be used for active control of the instability development. This conclusion is confirmed experimentally.
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页码：659 / 664
页数：6
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