Unsteady Numerical Analysis of a Dual-Mode Scramjet Combustor with a Cavity
Author:
Affiliation:
1. Department of Aeronautics and Astronautics, Tohoku University
2. Kakuda Space Center, Japan Aerospace Exploration Agency
Publisher
Japan Society for Aeronautical and Space Sciences
Subject
Space and Planetary Science,Aerospace Engineering
Link
https://www.jstage.jst.go.jp/article/tjsass/66/4/66_T-22-44/_pdf
Reference29 articles.
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2. 2) Jackson, K. R., Gruber, M. R., and Buccellato, S.: HIFiRE Flight 2 – A Program Overview, AIAA 2013-0695, 2013.
3. 3) Nakayama, H., Edanaga, T., Hashino, S., Tomioka, S., Kobayashi, K., and Takahashi, M.: A Dual-Mode Scramjet Combustor Employing a Jet Fuel for Hypersonic Flight Vehicle, AIAA 2018-4452, 2018.
4. 4) Choi, B., Takae, K., Kouchi, T., and Masuya, G.: Turbulent Characteristics for Jet Injected into Supersonic Flow with Pseudo Shock Wave, J. Propuls. Power, 28 (2012), pp. 971–981.
5. 5) Ben-Yakar, A. and Hanson, R. K.: Cavity Flame-Holders for Ignition and Flame Stabilization in Scramjets: An Overview, J. Propuls. Power, 17 (2001), pp. 869–877.
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