Simulation Study on Characteristic of Helicopter Nacelle Ventilation System in Forward Flight
Outflow field of helicopter has great effect on air flow of the inlet, the inside of nacelle and exhaust mixer as well as the Characteristics of nacelle cooling system in forward flight. Under the assumption that the size of the exhaust ejector is fixed, a simulation model of the Characteristics of helicopter nacelle cooling system in forward flight is established by considering the combination of the outflow field and exhaust ejector. To obtain precise calculation results, finite volume method and fully implicit method with coupling multi-grid solving technology are adopted in CFD software simulation. By the comparison and analysis of calculation results, it is showed that augmenting the size of inlet or putting inlet in the upper front of the nacelle could improve the performance of nacelle cooling system. And by setting the deflector cone in exhaust mixer, not only the velocity of air flow increases, but also the uniformity of exhaust mixers cross section is improved, which results in the decrease of temperature in the exhaust mixer and the improvement of the efficiency of the cooling system. The conclusions could be used as a reference for designing of nacelle cooling system.
helicopter nacelle forward flight numerical simulation flow field
Niu Xuemin Xie Yongqi Yu Jianzu
School of Aeronautical Science and Engineering,Beijing University of Aeronautics and Astronautics,Beijing 100191, China
国际会议
2010 Asia-Pacific International Symposium on Aerospace Technology(2010 亚太航空航天技术研讨会 APISAT 2010)
西安
英文
70-74
2010-09-01（万方平台首次上网日期，不代表论文的发表时间）