实验流体力学Issue(4)：59-64,6.DOI:10.11729/syltlx20130023
超声速/高超声速风洞试验段结构形式对流场性能的影响研究
Investigation of the performance of flow field in supersonic/hypersonic wind tunnel with different test section geometry configurations
杨波 1柳森1
作者信息
- 1. 中国空气动力研究与发展中心，四川 绵阳 621000
- 折叠
摘要
Abstract
The steady flow fields of the Ф1 m hypersonic wind tunnel are simulated under Mach number 3 and 6 by solving axisymmetric N-S equations.The comparison between the nu-merical simulation and experimental data validates that this numerical method is feasible.And then the flowfields of wind tunnels with closed straight round and unclosed free-jet test sections under these Mach numbers are simulated respectively.The results of uniformity test core of closed straight round and unclosed free-jet test sections meet the requirement of relevant stand-ards.The results show that the minimum diameter of the uniformity test core in Mach 3 nozzle with closed test section reaches Φ882mm at the axial coordinate from-300mm to 900mm.The test core increases by about 31.57% compared with free-jet test section,which significantly im-proves the test capacity of wind tunnel.For Mach 6 nozzle with closed test section,the uniformi-ty test core only increases by about 8.24% compared with unclosed test section,which makes lit-tle improvement on the flowfield performance.The uniformity test core of supersonic wind tun-nel with closed test section enlarges observably,but it is little larger in hypersonic wind tunnel with closed test section than that with unclosed free-jet test section.关键词
数值模拟/试验段结构/超声速风洞/流场品质Key words
numerical simulation/test section configuration/supersonic wind tunnel/flowfield performance分类
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杨波,柳森..超声速/高超声速风洞试验段结构形式对流场性能的影响研究[J].实验流体力学,2014,(4):59-64,6.
