Comparison of four boundary layer solutions for fuel regression ratein classical hybrid rocket motors
Author:
Affiliation:
1. Thiokol Corp., Brigham City, UT
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.1991-2520
Reference30 articles.
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1. Numerical and experimental investigation of throttleable hybrid rocket motor with aerospike nozzle;Aerospace Science and Technology;2020-11
2. Solid-Fuel Pyrolysis Phenomena and Regression Rate, Part 1: Mechanisms;Fundamentals of Hybrid Rocket Combustion and Propulsion;2007-05-01
3. Condensed-phase behavior and ablation rate of fuels for hybrid propulsion;29th Joint Propulsion Conference and Exhibit;1993-06-28
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