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A Numerical Simulation of Regenerative Cooling Heat Transfer for the Rocket Engine  

전종국 (한전원자력연료주식회사 열수력설계실)
박승오 (한국과학기술원 항공우주공학과)
Publication Information
Journal of the Korean Society of Propulsion Engineers / v.7, no.4, 2003 , pp. 46-52 More about this Journal
Abstract
This paper presents the numerical thermal analysis for regeneratively cooled rocket thrust chambers. An integrated numerical model incorporates computational fluid dynamics for the hot-gas thermal environment, and thermal analysis for the liner and coolant channels. The flow and temperature fields in rocket thrust chambers is assumed to be axisymmetric steady state which is presumed to the combustion liner. The heat flux computed from nozzle flow is used to predict the temperature distribution of the combustion liner As a result, we present the wall temperature of combustion liner and the temperature change of coolant.
Keywords
Nozzle; Regenerative Cooling; Cooling Channel;
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