Research on Fuel Mixing in a Non-reacting Situation Simulating a Dual-mode Combustor
Author:
Affiliation:
1. Department of Aerospace Engineering, Tohoku University
2. Kakuda Space Center, Japan Aerospace Exploration Agency
Publisher
Japan Society for Aeronautical and Space Sciences
Link
https://www.jstage.jst.go.jp/article/tastj/17/1/17_82/_pdf
Reference14 articles.
1. 1) Kanda, T. and Kudo, K.: Conceptual Study of a Combined-Cycle Engine for an Aerospace Plane, J. Propul. Power, 19 (2003), pp. 859-867.
2. 2) Mitani, T., Chinzei, N. and Kanda, T.: Reaction and Mixing- Controlled Combustion in Scramjet Engines, J. Propul. Power, 17(2001), pp. 308-314.
3. 3) Kouchi, T., Masuya, G., Hirano, K., Matsuo, A. and Tomioka, S.: Supersonic Combustion Using a Stinger-Shaped Fuel Injector, J. Propul. Power, 29 (2013), pp. 639-647.
4. 4) Torrence, M. G.: Effect of Injectant Molecular Weight on Mixing of a Normal Jet in a Mach 4 Airstream, NASA TN D-6061, 1971.
5. 5) Zakkay, V., Krause, E. and Woo, S. D. L.: Turbulent Transport Properties for Axisymmetric Heterogeneous Mixing, AIAA J., 2 (1964), pp. 1939-1947.
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