Pressure Distribution Measurements in Scramjet Isolators under Asymmetric Supersonic Flow
Author:
Affiliation:
1. Nanjing University of Aeronautics and Astronautics
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.2006-818
Reference14 articles.
1. Computational Fluid Dynamic Modelling of Pseudoshock Inside a Zero-Secondary Flow Ejector
2. 2D. B. Le, C. P. Goyne, R. H. Krauss, and J. C. McDaniel, "Experimental Study of a Dual-Mode Scramjet Isolator," AIAAPaper2005-0023,Jan.2005.
3. Kanenori Kato, Takeshi Kanda, Kan Kobayashi, Kenji Kudo, and Atsuo Murakami, "Experimental Study of DownstreamCombustionRamjet-Mode,"AIAAPaper2005-0617,Jan.2005.
4. Characteristics of multiple shock wave/turbulent boundary-layer interactions in rectangular ducts
5. Structure of Shock Waves in Cylindrical Ducts
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