Numerical investigation of lateral jets over body of revolution in supersonic crossflow

Abstract

In this paper, the flowfield induced by a sonic lateral jet in a supersonic crossflow of Mach number 3.3 around a body of revolution is numerically studied. The numerical simulation is first validated for the case of a circular nozzle. Shock and vortical structures are examined and compared with those of jet in crossflow over a flat plate. It is found that horseshoe vortices are generated from the flow separation region before the jet orifice. They are shed laterally along the footprint of the jet bow shock, wrapping the body of revolution. This wrapping effect is absent in the case of the crossflow over a flat plate. Effects of the jet nozzle shape on the flow structure are further investigated and analyzed. These nozzles, including circular, elliptical, dropletlike, and inverse dropletlike shapes, have equivalent cross-sectional area. The elliptical nozzle with its semimajor axis in the lateral direction has the largest force amplification factor and is thus the most effective. The detailed flow structures also indicate that the low-pressure region aft of the jet is not only closely related with the surface trailing vortices, but also with the indent and reflection lines of the leeward barrel shock. Copyright © 2011 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.