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Suppression of transonic buffet with plasma vortex generators

Suppression of transonic buffet with plasma vortex generators In the present paper, we report on the results of an experimental study of the possibility to control the transonic buffet on a rectangular wing using plasma vortex generators. The influence of the developed device on the flow consists in creating a longitudinal vortex in the boundary layer as a result of asymmetric energy supply at the surface of a small vertical wedge. The experiments were performed using a wing model with a supercritical airfoil in the range of free-stream Mach numbers 0.73 to 0.78 and Reynolds numbers Re = (2.64-2.8)·106. The experimental data obtained using the method of high-speed schlieren visualization and pressure distribution measurements in the wake of the model show that the technique allows one to control both the average flow characteristics and the characteristics of shock-wave oscillations. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png Thermophysics and Aeromechanics Springer Journals

Suppression of transonic buffet with plasma vortex generators

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Publisher
Springer Journals
Copyright
Copyright © 2019 by A.A. Sidorenko, A.D. Budovsky, P.A. Polivanov, O.I. Vishnyakov, V.G. Sudakov, and V.N. Ishchenko
Subject
Physics; Thermodynamics
ISSN
0869-8643
eISSN
1531-8699
DOI
10.1134/S0869864319040012
Publisher site
See Article on Publisher Site

Abstract

In the present paper, we report on the results of an experimental study of the possibility to control the transonic buffet on a rectangular wing using plasma vortex generators. The influence of the developed device on the flow consists in creating a longitudinal vortex in the boundary layer as a result of asymmetric energy supply at the surface of a small vertical wedge. The experiments were performed using a wing model with a supercritical airfoil in the range of free-stream Mach numbers 0.73 to 0.78 and Reynolds numbers Re = (2.64-2.8)·106. The experimental data obtained using the method of high-speed schlieren visualization and pressure distribution measurements in the wake of the model show that the technique allows one to control both the average flow characteristics and the characteristics of shock-wave oscillations.

Journal

Thermophysics and AeromechanicsSpringer Journals

Published: Nov 26, 2019

References