Direct-connect supersonic nozzle design considering the effect of combustion
Author:
Funder
Agency for Defense Development
Defense Acquisition Program Administration
Publisher
Elsevier BV
Subject
Aerospace Engineering
Reference11 articles.
1. Design of a Mach 2 shape transition nozzle for lab-scale direct-connect supersonic combustor;Sung;Aerosp. Sci. Technol.,2021
2. Thermochemical performance analysis of liquid rocket nozzle;Choi;J. Korean Soc. Aeronaut. Space Sci.,2003
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5. Numerical model for nozzle flow application under liquid oxygen/methane hot-flow conditions;Schneider;J. Propuls. Power,2018
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