Delayed Detached Eddy Simulation of a Transverse Supersonic Jet into Hypersonic Crossflow

In both military and civil industries, the complex flow field induced by a jet exhausting has widespread applications, such as supersonic/hypersonic vehicle reaction control systems, thrust vector control systems on rocket motors, and supersonic combustion. The jet interaction flow field involves complex unsteady shocks, spatial vortex, and separated flow and shear layer; the traditional Reynolds-averaged Navier–Stokes equations failed to predict these unsteady characteristics and perform poor in separated flow. In this study, the supersonic jet exhausting into a hypersonic crossflow is investigated by the delayed detached eddy simulation (DDES). The typical mean flow properties and the instantaneous flow properties are analyzed. Results show that calculated data agreed well with the experimental data. DDES is also capable of resolving and capturing the detailed flow structures.