Transient interaction between a reaction control jet and a hypersonic crossflow

Abstract

This paper presents a numerical study that focuses on the transient interaction between a reaction control jet and a hypersonic crossflow with a laminar boundary layer. The aim is to better understand the underlying physical mechanisms affecting the resulting surface pressure and control force. Implicit large-eddy simulations were performed with a round, sonic, perfect air jet issuing normal to a Mach 5 crossflow over a flat plate with a laminar boundary layer, at a jet-to-crossflow momentum ratio of 5.3 and a pressure ratio of 251. The pressure distribution induced on the flat plate is unsteady and is influenced by vortex structures that form around the jet. A horseshoe vortex structure forms upstream, and consists of six vortices: two quasi-steady vortices and two co-rotating vortex pairs that periodically coalesce. Shear-layer vortices shed periodically and cause localised high pressure regions that convect downstream with constant velocity. A longitudinal counter-rotating vortex pair is present downstream of the jet, and is formed from a series of trailing vortices which rotate about a common axis. Shear-layer vortex shedding causes periodic deformation of barrel and bow shocks. This changes the location of boundary layer separation which also affects the normal force on the plate. * warrick.miller@adelaide.edu.au.

Experimental investigation of sonic transverse jets in Mach 5 crossflow

“…In addition various authors examined jets in supersonic cross flow in a scramjet engine, numerically [27], [28], [29], [30]. Specifically Miller et al [25] numerically investigated transient interaction between a reaction control jet and Mach 5 cross flow using data from the thesis of Erdem [26]. The aim was to understand the mechanism of side force generation due to surface pressure distribution using Large Eddy Simulation (LES).…”

Effectiveness of multiple jets for a finned large slenderness ratio missile in supersonic crossflows

“…Typically, for slender bodies, missiles as an example, the high-pressure region wraps around the configuration to the reverse side of jets which has a negative effect on jet effectiveness. 10 A number of numerical studies have been carried out for jet-in-crossflow problems by solving Reynolds-averaged Navier-Stokes (RANS) 6,13 , deteched eddy simulation 14 , and large-eddy simulation 15 equations. Huh 16 investigated the effect of turbulence models and numerical flux functions for sonic jet ejected from a generic missile at Mach 3.…”