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Aerospace 2015, 2(1), 118-134; doi:10.3390/aerospace2010118

Supersonic Flow Control Using Combined Energy Deposition

Department of Mathematical Modeling of Computer-Aided Design Systems, Dorodnicyn Computing Centre of the Russian Academy of Sciences, Vavilova str. 40, Moscow 119333, Russia
The results of this paper were presented at the 51st AIAA Aerospace Sciences Meeting (Grapevine, Texas, USA, 7–10 January 2013) and the 21st International Shock Interaction Symposium (Riga, Latvia, 3–8 August 2014).
Academic Editor: Hossein Zare-Behtash
Received: 29 January 2015 / Revised: 6 March 2015 / Accepted: 13 March 2015 / Published: 18 March 2015
(This article belongs to the Special Issue Recent Advances in SWBLI Research)
View Full-Text   |   Download PDF [21907 KB, uploaded 18 March 2015]   |  

Abstract

Drag force control via energy deposition in an oncoming flow is a wide area of interest in aerospace sciences. Recently, investigations on the effect of combining energy sources have been conducted. The possibility of coupling microwave (MW) discharges or MW and laser energy deposition is discussed. In the present work, the flow details accompanying the interaction of a combined energy release and an aerodynamic body in a supersonic flow are considered numerically on the base of the Euler equations. Comparison with non-combined energy deposition is analyzed. The effect of introducing the internal part to the energy release on the drag force reduction is examined. The flows for blunt cylinder, hemisphere-cylinder and pointed body are considered for a wide class of the combined energy source characteristics. Freestream Mach number is varied from 1.89 to 3.45. Complicated unsteady vortex structures caused by the Richtmyer–Meshkov instabilities are shown to be the reason for the reduction in drag. The unsteady double vortex mechanism of the frontal drag force reduction and mechanism of the constantly acting vortices at the steady flow are described. Suppression of shear layer instability and large scaled flow pulsations as the result of the combined energy release effect is established. Complex conservative difference schemes are used in the simulations. View Full-Text
Keywords: combined energy deposition; drag force control; complex conservative difference schemes combined energy deposition; drag force control; complex conservative difference schemes
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This is an open access article distributed under the Creative Commons Attribution License which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited. (CC BY 4.0).

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Azarova, O.A. Supersonic Flow Control Using Combined Energy Deposition. Aerospace 2015, 2, 118-134.

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