Analysis of Separation Modes Variation in a Scramjet Combustor with Single-Side Expansion
Author:
Affiliation:
1. National University of Defense Technology, 410073 Changsha, People’s Republic of China
Funder
National Natural Science Foundation of China
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
https://arc.aiaa.org/doi/pdf/10.2514/1.J055411
Reference30 articles.
1. Experimental Investigation of Supersonic Model Combustor with Distributed Injection of Supercritical Kerosene
2. Asymmetry effects in numerical simulation of supersonic flows with upstream separated regions
3. Asymmetric flow-structures in dual mode scramjet combustor with significant upstream interaction
4. Ram-Scram Transition and Flame/Shock-Train Interactions in a Model Scramjet Experiment
5. Fundamental Investigation of Supersonic Nozzle Flow Separation
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