@inproceedings{b3c00a5ee79c4e499e894201a15897b0,
title = "Simulation of supersonic turbulent non-reactive flow in ramp-cavity combustor using a discontinuous spectral element method",
abstract = "The flow inside the combustion chamber of a scramjet engine is a prime example of multi-scale and multi-physics flow and is often accompanied by the concurrent presence of shock waves and turbulence. In this work, a high-order discontinuous spectral element method (DSEM) is employed to simulate the supersonic non-reactive flow inside a ramp-cavity combustor. The Mach number is Ma = 2. An entropy viscosity method is implemented to capture the shocks, and the standard Smagorinsky-Lilly model is used as the turbulence model. Results are presented for two simulations with and without an injector and the results are compared. The effect of the Reynolds number is also studied. Stronger mixing effects are observed within the cavity for the case with the injector. Higher Reynolds number also results in a steeper and stronger shock and reflection waves.",
author = "Z. Ghiasi and J. Komperda and D. Li and F. Mashayek",
note = "Publisher Copyright: {\textcopyright} 2016, American Institute of Aeronautics and Astronautics Inc, AIAA. All Rights Reserved.; 54th AIAA Aerospace Sciences Meeting, 2016 ; Conference date: 04-01-2016 Through 08-01-2016",
year = "2016",
doi = "10.2514/6.2016-0617",
language = "English (US)",
isbn = "9781624103933",
series = "54th AIAA Aerospace Sciences Meeting",
publisher = "American Institute of Aeronautics and Astronautics Inc, AIAA",
booktitle = "54th AIAA Aerospace Sciences Meeting",
}