Next Article in Journal
Gust Alleviation of a Large Aircraft with a Passive Twist Wingtip
Next Article in Special Issue
Numerical Study of Shock Wave Attenuation in Two-Dimensional Ducts Using Solid Obstacles: How to Utilize Shock Focusing Techniques to Attenuate Shock Waves
Previous Article in Journal
The Development of Rocketry Capability in New Zealand—World Record Rocket and First of Its Kind Rocketry Course
Previous Article in Special Issue
Shock Wave Diffraction Phenomena around Slotted Splitters
Open AccessArticle

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
Aerospace 2015, 2(1), 118-134;
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)
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
Show Figures

Figure 1

MDPI and ACS Style

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

Show more citation formats Show less citations formats

Article Access Map by Country/Region

Only visits after 24 November 2015 are recorded.
Back to TopTop