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乘波飞行器的优化设计和气动热计算研究
引用本文:梅东牧,武哲,李天. 乘波飞行器的优化设计和气动热计算研究[J]. 航空计算技术, 2008, 38(6): 13-16
作者姓名:梅东牧  武哲  李天
作者单位:北京航空航天大学,航空科学与工程学院,北京,100083;沈阳飞机设计研究所,辽宁,沈阳,110035
摘    要:以高超声速技术为研究背景,开展高超声速乘波飞行器设计方法研究.在已有乘波构型生成方法基础上,采用相交楔锥生成多级压缩的乘波构形.并通过对乘波器的前缘进行钝化,进行了气动热特性数值研究.使乘波体在气动力层面上具有尖前缘,保持高升阻比特性,而在气动热层面上具有钝前缘,降低气动加热强度.结果表明,这为高超声速飞行器的气动防热设计开辟了新途径.

关 键 词:高超声速乘波飞行器  气动热  数值模拟

Research of the Waverider Optimization Design and Aerothermodynamics
MEI Dong-mu,WU Zhe,LI Tian. Research of the Waverider Optimization Design and Aerothermodynamics[J]. Aeronautical Computer Technique, 2008, 38(6): 13-16
Authors:MEI Dong-mu  WU Zhe  LI Tian
Affiliation:MEI Dong-mu1,WU Zhe1,LI Tian2(1.School of Aeronautics Science , Technology,Beijing University of Aeronautics , Astronautics,Beijing 100083,China,2.Shenyang Aircraft Design , Research Institute,Shenyang 110035,China)
Abstract:To study hypersonic technology,several methods are investigated to design Waverider aerodynamic configuration.Base on the study of waverider,a new conceptual hypersonic waverider is designed by showing a sharp leading edge in aerodynamic perspective and an artificially blunt leading edge,in aerothermal perspective.The results show that it can be used for the design of aerothermodynamics.
Keywords:hypersonic waverider  aerothermodynamics  numerical simulation  
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