Factors affecting flow separation in contoured supersonic nozzles.
Author:
Affiliation:
1. Southern Methodist University Institute of Technology, Dallas, Texas
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/3.4693
Reference9 articles.
1. Campbell, C. E. and Farley, J. M. "Performance of Several Conical Convergent-Divergent Rocket-Type Exhaust Nozzles/' TN D-467, 1960, NASA.
2. SHOCK-INDUCED BOUNDARY LAYER SEPARATION IN OVER-EXPANDED CONICAL EXHAUST NOZZLES
3. Investigation of Supersonic Flow Separation in Nozzles
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