Computational fluid dynamics investigation of a mach 12 scramjet engine

Moule, Yann, Sabel'Nikov, Vladimir, Mura, Arnaud and Smart, Michael (2014) Computational fluid dynamics investigation of a mach 12 scramjet engine. Journal of Propulsion and Power, 30 2: 461-473. doi:10.2514/1.B34992


Author Moule, Yann
Sabel'Nikov, Vladimir
Mura, Arnaud
Smart, Michael
Title Computational fluid dynamics investigation of a mach 12 scramjet engine
Journal name Journal of Propulsion and Power   Check publisher's open access policy
ISSN 0748-4658
1533-3876
Publication date 2014-03-01
Year available 2014
Sub-type Article (original research)
DOI 10.2514/1.B34992
Open Access Status
Volume 30
Issue 2
Start page 461
End page 473
Total pages 13
Place of publication Reston, VA, United States
Publisher American Institute of Aeronautics and Astronautics
Language eng
Abstract The description of combustion in high-speed turbulent flows, where turbulent mixing, compressibility effects, and chemical kinetics processes are competing, still remains a challenging issue for numerical simulations. The key features of such turbulent supersonic reactive flows are integrated into a turbulence-chemistry interaction closure, which relies on the partially stirred reactor framework. The corresponding closure, hereafter denoted as the unsteady partially stirred reactor model, is incorporated into the ONERA computational fluid dynamics code CEDRE. The computational model is used to investigate a Mach 12 rectangular-to-elliptical-shape-transition scramjet engine developed and operated at the University of Queensland. Results of Reynolds-averaged Navier-Stokes numerical simulations based on either the unsteady partially stirred reactor concept or the classical quasi-laminar closure are presented and compared. Similar results in terms of pressure distributions are obtained, thus confirming that the essential point to cope with such scramjet engine conditions is to represent satisfactorily the compressible flowfield. The Reynolds-averaged Navier-Stokes numerical simulations are subsequently used to investigate the engine performance, through the calculation of energetic efficiencies. The obtained results bring useful insights into the classical quasi-one-dimensional performance analyses. In particular, the inlet injection scheme is found to display the best performance with a combustion efficiency of 78%.
Keyword Engineering, Aerospace
Engineering
Q-Index Code C1
Q-Index Status Confirmed Code
Institutional Status UQ
Additional Notes Published March-April 2014.

Document type: Journal Article
Sub-type: Article (original research)
Collections: School of Mechanical & Mining Engineering Publications
Official 2015 Collection
 
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