Effect of nozzle boundary layers on rocket exhaust plumes.
Author:
Affiliation:
1. Avco Everett Research Laboratory, Everett, Mass.
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/3.6656
Reference8 articles.
1. Exhaust plumes from nozzles with wall boundary layers.
2. Rapid expansion of a supersonic boundary layer and its application to the near wake.
3. Hypersonic boundary-layer separation and the base flow problem.
4. FAR-FIELD APPROXIMATION FOR A NOZZLE EXHAUSTING INTO A VACUUM
5. Analytical approximation for the flow from a nozzle into a vacuum.
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