Numerical study on cavity ignition process in a supersonic combustor
Author:
Funder
National Natural Science Foundation of China
the Postdoctoral Innovation Talent Support Program of China
Publisher
Zhejiang University Press
Subject
General Engineering
Link
https://link.springer.com/content/pdf/10.1631/jzus.A1900419.pdf
Reference35 articles.
1. Barnes FW, Segal C, 2015. Cavity-based flameholding for chemically-reacting supersonic flow. Progress in Aerospace Sciences, 76:24–41. https://doi.org/10.1016/j.paerosci.2015.04.002
2. Baurle RA, Mathur T, Gruber MR, et al., 1998. A numerical and experimental investigation of a scramjet combustor for hypersonic missile applications. Proceedings of the 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. https://doi.org/10.2514/6.1998-3121
3. Ben-Yakar A, Hanson RK, 2001. Cavity flame-holders for ignition and flame stabilization in scramjets: an overview. Journal of Propulsion and Power, 17(4):869–877. https://doi.org/10.2514/2.5818
4. Beresh SJ, Wagner JL, Casper KM, 2016. Compressibility effects in the shear layer over a rectangular cavity. Journal of Fluid Mechanics, 808:116–152. https://doi.org/10.1017/jfm.2016.540
5. Cai Z, Liu X, Gong C, et al., 2016. Large eddy simulation of the fuel transport and mixing process in a scramjet combustor with rearwall-expansion cavity. Acta Astronautica, 126:375–381. https://doi.org/10.1016/j.actaastro.2016.05.010
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