한국항공운항학회지 (Journal of the Korean Society for Aviation and Aeronautics)
- 제14권1호
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- Pages.2-8
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- 2006
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- 1225-9705(pISSN)
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- 2466-1791(eISSN)
하이브리드 로켓 인젝터 포트직경 변화에 따른 난류연소 유동장 해석
Investigation of Turbulent Combustion Characteristics for Different Injector Port Diameter in Hybrid Rocket
초록
Numerical analysis of the flow field in the reactive medium of End-Burring combustor is studied in order to investigate the combustion characteristics of hybrid combustion. The main part of this study is focused on the port diameter effects of oxidizer injector on the temperature distribution within the reactive field. It is found that the case having the largest port diameter(25 mm) delivers the optimum conditions for the design of End-Burring combustor where the predicted temperature field showed the most acceptable distribution.