定/变热线过热比跨超声速流场湍流度测量  

Keeping and varying hot wire overheat ratio measurement for turbulence level in transonic and supersonic flow field

作　　者：朱博[1] 熊波 吴巍 王宁[1] ZHU Bo;XIONG Bo;WU Wei;WANG Ning(Facility Design and Instrumentation Institute,China Aerodynamics Research and Development Center,Mianyang Sichuan 621000,China;High Speed Aerodynamics Institute,China Aerodynamics Research and Development Center,Mianyang Sichuan 621000,China)

机构地区：[1]中国空气动力研究与发展中心设备设计与测试技术研究所,四川绵阳621000 [2]中国空气动力研究与发展中心高速空气动力研究所,四川绵阳621000

出　　处：《航空动力学报》2022年第9期1815-1823,共9页Journal of Aerospace Power

基　　金：空气动力学国家重点实验室基金(JBKY15040501)。

摘　　要：开展了基于定、变热线过热比方法测量跨超声速流场湍流度的比较研究,以满足高速飞行器与发动机的跨超声速风洞高精度实验需求。在1.2 m暂冲式跨超声速风洞上,采用定过热比、变二过热比和变八过热比等三种热线测量方法,完成了马赫数为0.30~4.25的跨超声速流场湍流度测量研究。测量结果表明:变八过热比测量精度最高,实测湍流度的蒙特卡洛模拟不确定度为0.001%~0.033%;定过热比方法与变二过热比方法可实现更快速的测量,在马赫数为0.40~2.00范围内与变八过热比测量湍流度均值偏差约9%~18%。研究结果对跨超声速流场湍流度校测、飞行器实验鉴定和数值计算具有实际助益。A research comparison for keeping and varying hot wire overheat ratio measurement for turbulence level in transonic and supersonic flow field was carried out to satisfy the need of high precision testing of high speed aircraft and engine in transonic and supersonic wind tunnels.Three methods including keeping hot wire overheat ratio,varying two hot wire overheat ratios,and varying eight hot wire overheat ratios,were used for measuring turbulence level at Mach number of 0.30-4.25 in a 1.2 m blow down transonic and supersonic wind tunnel.The measurement result showed that,the method of varying eight hot wire overheat ratio was most precise,and Monte Carlo simulation uncertainty was around 0.001%-0.033% for measuring turbulence level.Methods of keeping and varying two hot wire overheat ratio realized more fast measurement,bias of mean turbulence level comparing with varying eight hot-wire overheat ratios was around 9%-18% at Mach number of 0.40-2.00.The research result was practical for flow turbulence evaluation,aircraft test evaluation and numerical calculation in transonic and supersonic flow fields.

关 键 词：跨超声速流 湍流度 热线风速仪 暂冲式风洞 流场校测 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]