跨声速流场扰动模态与湍流度精细测量  

Fine measurement for fluctuation mode and turbulence level in transonic flow

作　　者：朱博[1] 廖达雄[1,2] 陈振华[1] 陈吉明[1,2] ZHU Bo;LIAO Daxiong;CHEN Zhenhua;CHEN Jiming(Facility Design and Instrumentation Institute,China Aerodynamics Research and Development Center,Mianyang 621000,China;State Key Laboratory of Aerodynamics,China Aerodynamics Research and Development Center,Mianyang 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,绵阳621000 [2]中国空气动力研究与发展中心空气动力学国家重点实验室,绵阳621000

出　　处：《航空学报》2023年第4期124-135,共12页Acta Aeronautica et Astronautica Sinica

基　　金：空气动力学国家重点实验室基金(JBKY15040501)。

摘　　要：开展了跨声速风洞可压流场扰动模态与湍流度精细测量研究,以满足高速飞行器的低湍流试验需求。基于变热线过热比测量方法,在理论上推导了跨声速流场扰动的一般模态和3种特殊模态特征方程(涡模态、熵模态和声模态),以及扰动模态对应的特征曲线,以此为基础,通过试验获得了流场一般模态、涡模态、声模态扰动图和较高精度的湍流度值,通过扰动图频域分析了马赫数1.50的流场声模态扰动机理,建立了一种跨声速可压流场扰动模态分析与低湍流度测量方法。在新型连续式跨声速风洞完成马赫数0.20~1.50流场测量试验,测得湍流度为0.037%~0.197%,数据非线性拟合优度为0.943~0.995,蒙特卡洛模拟不确定度为0.0002%~0.0041%。研究结果证明了所建立的可压流场扰动模态与低湍流度测量方法的有效性,对高性能跨声速风洞的流场评估、优化和飞行器低湍流试验有实际意义。Fine measurement for the compressible flow fluctuation mode and turbulence level in transonic wind tunnels is studied to satisfy the need of low turbulence flow tests for high speed aircraft.Based on the measurement of varying hot wire overheat ratio,we derive the functions of the general mode and three special modes including the vorticity mode,the entropy mode and the acoustic mode for transonic flow fluctuations.An experiment is then conducted based on this method,obtaining fluctuation diagrams of the general mode,the vorticity mode,and the acoustic mode,calculating a high accuracy turbulence level,adopting fluctuation diagram analysis in frequency domain to ratio⁃nalize the flow mechanism at Ma 1.50,and building a measurement method for the fluctuation mode and the low tur⁃bulence level.When the Mach number varies from 0.20 to 1.50 in the new type continuous transonic wind tunnel,the turbulence level is around 0.037%-0.197%,with the nonlinear function fitness goodness of data around 0.943-0.995 and the Monte Carlo simulation uncertainty around 0.0002%-0.0041%.Results show the effectiveness of the mea⁃surement method for the fluctuation mode and low turbulence level,exhibiting practical value for flow field quality evaluation and optimization,and low turbulence test of high speed aircraft in high-performance transonic wind tunnels.

关 键 词：可压缩流 扰动模态 湍流度 热线风速仪 跨声速风洞 连续式风洞 

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] O357.5[理学—流体力学]