航空工业1m量级高超声速风洞设计与建设进展

Design and construction progress of AVICΦ1.0m hypersonic wind tunnel

航空工业1 m量级高超声速风洞(FL-64)是国内最新建设的一座暂冲自由射流式大口径常规高超声速风洞,采用吹引式运行方式,同时考虑到低动压试验需要,另建有真空抽气系统。详细介绍了FL-64风洞的总体性能指标、关键部段设计、流场校测和标模试验结果。风洞性能指标如下:模拟马赫数范围4.0~8.0;总压范围0.1~8.0 MPa;总温范围300~900 K;单位雷诺数范围3.3×10^(6)~4.6×10^(7)m^(–1);有效运行时间不小于30 s。FL-64风洞与航空工业亚跨超三声速风洞(FL-60)可形成高低马赫数搭配,涵盖马赫数0.3~8.0的宽速域高超声速飞行器试验需求,特别是马赫数4.0的总焓模拟能力可与真实飞行条件匹配,为我国高马赫数飞行器研制提供有效的气动试验平台。

The 1 m hypersonic wind tunnel for the AVIC(FL-64)is the newly built blow down free jet type large-diameter conventional hypersonic wind tunnel in China.It adopts the blowing type operation mode,at the same time,considering the test requirements of low dynamic pressure,a vacuum exhaust system is also equipped.The overall performance,key component design,flow field calibration and preliminary standard model test results of the FL-64 wind tunnel are presented in detail.The performance of the wind tunnel are as follows:the range of Mach number:4.0-8.0;the total pressure range of the settling chamber:0.1-8.0 MPa;the total temperature range of the settling chamber:300-900 K;the unit Reynolds number range:3.3×10^(6)-4.6×10^(7)m^(-1);the effective operating time is not less than 30 s.The FL-64 wind tunnel combined the FL-60 trisonic(Subsonic,Transonic,Supersonic)wind tunnel forming the high and low Mach number range,this can cover the wide-speed range aircraft test with a Mach number of 0.3-8.0.Especially the duplication capability of the total enthalpy of Mach number 4.0 can match the real flight conditions.Overall,the successful completion of the FL-64 wind tunnel provide an effective test platform for the development of nation’s high Mach number aircraft.