Computational investigation of thermal nonequilibrium effects in scramjet geometries

Gehre, R. M., Wheatley, V. and Boyce, R. R. (2013) Computational investigation of thermal nonequilibrium effects in scramjet geometries. Journal of Propulsion and Power, 29 3: 648-660. doi:10.2514/1.B34722

Author Gehre, R. M.
Wheatley, V.
Boyce, R. R.
Title Computational investigation of thermal nonequilibrium effects in scramjet geometries
Journal name Journal of Propulsion and Power   Check publisher's open access policy
ISSN 0748-4658
Publication date 2013-05-01
Year available 2013
Sub-type Article (original research)
DOI 10.2514/1.B34722
Open Access Status Not yet assessed
Volume 29
Issue 3
Start page 648
End page 660
Total pages 13
Place of publication Reston, VA, United States
Publisher American Institute of Aeronautics and Astronautics
Language eng
Subject 2103 Fuel Technology
2202 Aerospace Engineering
2210 Mechanical Engineering
1912 Space and Planetary Science
Abstract To characterize the impact of thermal nonequilibrium in shock-induced combustion scramjets, several thermal equilibrium and nonequilibrium computational fluid dynamics simulations have been performed. Specifically, the effects that would be encountered in shock-tunnel testing are of interest. Therefore, thermal equilibrium and nonequilibrium simulations are run for a Mach 6 shock-tunnel nozzle and a radical farming scramjet model with total enthalpies between 3.3 and 4.9 MJ/kg. Simulating both the nozzle and scramjet with thermal nonequilibrium represents the shock-tunnel test, whereas equilibrium inflow into a scramjet simulated in thermal nonequilibrium provides the scenario encountered in actual flight. For all nonequilibrium simulations, the Landau-Teller model in combination with modified Millikan and White thermal relaxation coefficients is used. It is shown that modeling the entire flow as being in thermal equilibrium results in higher effective temperatures within the local high-temperature regions where ignition occurs, which causes the ignition length to decrease and thus the combustion process to be more efficient compared with the nonequilibrium cases. Additionally, the conditions for ignition in simulations representing shock-tunnel experiments are found to be more favorable than in the simulations representing a flight test, assuming the same enthalpy and boundary conditions. Furthermore, these differences are found to be insensitive to the total enthalpy.
Keyword Engineering, Aerospace
Q-Index Code C1
Q-Index Status Confirmed Code
Institutional Status UQ
Additional Notes Published online: 27 March 2013.

Document type: Journal Article
Sub-type: Article (original research)
Collections: School of Mechanical & Mining Engineering Publications
Official 2014 Collection
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Citation counts: TR Web of Science Citation Count  Cited 4 times in Thomson Reuters Web of Science Article | Citations
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