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Wave processes in a viscous shock layer and control of fluctuations

Published online by Cambridge University Press:  18 March 2010

A. A. MASLOV ,
S. G. MIRONOV ,
A. N. KUDRYAVTSEV ,
T. V. POPLAVSKAYA  and
I. S. TSYRYULNIKOV
A. A. MASLOV
Affiliation:
Khristianovich Institute of Theoretical and Applied Mechanics, Novosibirsk 630090, Russia Department of Physics, Novosibirsk State University, Novosibirsk 630090, Russia
S. G. MIRONOV
Affiliation:
Khristianovich Institute of Theoretical and Applied Mechanics, Novosibirsk 630090, Russia Department of Physics, Novosibirsk State University, Novosibirsk 630090, Russia
A. N. KUDRYAVTSEV
Affiliation:
Khristianovich Institute of Theoretical and Applied Mechanics, Novosibirsk 630090, Russia Department of Physics, Novosibirsk State University, Novosibirsk 630090, Russia
T. V. POPLAVSKAYA*
Affiliation:
Khristianovich Institute of Theoretical and Applied Mechanics, Novosibirsk 630090, Russia Department of Physics, Novosibirsk State University, Novosibirsk 630090, Russia
I. S. TSYRYULNIKOV
Affiliation:
Khristianovich Institute of Theoretical and Applied Mechanics, Novosibirsk 630090, Russia Department of Physics, Novosibirsk State University, Novosibirsk 630090, Russia
*
†Email address for correspondence: popla@itam.nsc.ru
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Abstract

Generation and development of disturbances in a hypersonic viscous shock layer on a flat plate is studied both experimentally and numerically. The study is performed at the Mach number M∞ = 21 and the Reynolds number ReL = 1.44 × 105 and is aimed at elucidating the physical mechanisms that govern the receptivity and instability of the shock layer at extremely high hypersonic velocities. The experiments are conducted in a hypersonic nitrogen-driven wind tunnel. An electron-beam fluorescence technique, a Pitot probe and a piezoceramic transducer are used to measure the mean density and Mach number contours, as well as density and pressure fluctuations, their spectra and spatial distributions in the shock layer. Direct numerical simulations are performed by solving the Navier–Stokes equations with a high-order shock-capturing scheme in a computational domain including the leading and trailing edges of the plate, so that the bow shock wave and the wake behind the plate are also simulated. It is demonstrated that computational and experimental data characterizing the mean flow field, intensity of density fluctuations and their spatial distributions in the shock layer are in close agreement. It is found that excitation of the shock layer by external acoustic waves leads to generation of entropy–vortex disturbances with two maxima of density fluctuations: directly behind the shock wave and on the external edge of the boundary layer. At the same time, the pressure fluctuations decay inward into the shock layer, away from the shock, which agrees with the linear theory of interaction of shock waves with small perturbations. Thus, the entropy–vortex disturbances are shown to dominate in the hypersonic shock layer at very high Mach numbers, in contrast with the boundary layers at moderate hypersonic velocities where acoustic modes are most important. A parametric numerical study of wave processes in the shock layer induced by external acoustic waves is performed with variations of frequency, amplitude and angle of propagation of external disturbances. The amplitude of generated disturbances is observed to grow and decay periodically along the streamwise coordinate, and the characteristics of these variations depend on the frequency and direction of incident acoustic waves. The hypersonic shock layer excited by periodic blowing and suction near the leading edge is also investigated; in the experiments, this type of excitation is obtained by using an oblique-cut whistle. It is shown that blowing/suction generates disturbances resembling those generated by external acoustic waves, with similar spatial distributions and phase velocities. This result paves the way for active control of instability development in the shock layer by means of destructive interference of two types of disturbances. Numerical simulations are performed to show that instability waves can be significantly amplified or almost entirely suppressed, depending on the relative phase of blowing/suction and acoustic disturbances. Wind-tunnel experiments completely confirm this numerical prediction. Thus, the feasibility of delaying instability development in the hypersonic shock layer has been demonstrated for the first time.

Type
Papers
Information
Journal of Fluid Mechanics , Volume 650 , 10 May 2010 , pp. 81 - 118
Copyright
Copyright © Cambridge University Press 2010

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References

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