Convergence of Two Analytical Flowfield Models Predicting a Destabilizing Agent in Rocket Combustion
Author:
Affiliation:
1. Marquette University, Milwaukee, Wisconsin 53233
2. University of Tennessee Space Institute, Tullahoma, Tennessee 37388
3. California Institute of Technology, Pasadena, California 91125
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Space and Planetary Science,Mechanical Engineering,Fuel Technology,Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/2.5595
Reference12 articles.
1. On flow turning
2. Improved Time-Dependent Flowfield Solution for Solid Rocket Motors
3. Boundary-Layer Structure in Cylindrical Rocket Motors
4. Effects of vorticity on rocket combustion stability
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