摘要
在分析国内外高超声速风洞发展现状的基础上,根据南京航空航天大学高超声速风洞(Nanjing Universityof Aeronautics&Astronautics Hypersonic Wind Tunnel,NHW)总体技术指标和要求,对该风洞气动布局设计方案和各部件的气动设计进行了研究。风洞气动布局设计点为马赫数5和8、设计总压为1 MPa、总温685 K;风洞驱动方式采用高压下吹-真空吸气式方案,运行时间大于10 s、高压气源容积为32 m3、真空容积为650 m3;风洞加热方式采用金属板蓄热式加热器方案;风洞试验马赫数获取方式采用0.5 m口径的马赫数5,6,7和8的型面喷管方案。
By analyzing the development of hypersonic wind tunnels in the world, a detailed scheme is presented for Nanjing University of Aeronautics ＆ Astronautics Hypersonic Wind Tunnel （NHW）, and it is the indices and the requirements of NHW. Operational conditions are as follows： essential design Mach numbers are 5 and 8, upstream-chamber stagnation pressure is 1 MPa, stagnation temperature is 685 K, running time is more than 10 s. The volumes of high pressure air supply system and the vacuum system are 32 m^3 and 650 m^3, respectively. The wind tunnels is heated with the storage heater. Testing Mach numbers 5, 6, 7 and 8 are realized by using the contour nozzle with the exit-diameter of 0.5 m.
出处
《南京航空航天大学学报》
CAS
CSCD
北大核心
2008年第2期271-274,共4页
Journal of Nanjing University of Aeronautics & Astronautics
关键词
高超声速
风洞
气动布局
hypersonic
wind tunnels
aerodynamic configuration
