尖楔模型结构对脉动压力测量影响实验研究  

Experimental Study of the Wedge Model Structure Effect on the Pressure Fluctuation Measurement

作　　者：沙心国[1] 李睿劬[1] 刘文伶[2] 纪锋[1] 袁湘江[1] SHA Xin-guo;LI Rui-qu;LIU Wen-ling;JI Feng;YUAN Xiang-jiang(China Academy of Aerospace Aerodynamics, Beijing 100074, China;Beijing Institute of Space Long March Vehicle, Beijing 100076, China)

机构地区：[1]中国航天空气动力技术研究院,北京100074 [2]北京航天长征飞行器研究所,北京100076

出　　处：《气体物理》2021年第3期43-49,共7页Physics of Gases

基　　金：国家重点研发计划资助项目(2019YFA0405300,2019YFA0405200)。

摘　　要：高超声速边界层转捩与湍流研究是当前空气动力学研究的一个热门领域,脉动压力测量技术在高超声速风洞背景噪声测量和边界层内扰动波发展研究实验中得到了广泛应用.脉动压力传感器由于灵敏度高、测量频率范围宽,其测量结果受多方面因素影响.文章以尖楔模型为研究对象,在常规高超声速风洞中开展了模型背面凸起对表面脉动压力测量结果影响的实验研究,获得了3种背面结构(方型凸起、斜坡型凸起和无凸起)模型表面脉动压力信息,对比发现模型背面方型凸起和斜坡型凸起使得模型表面声压级明显增加,其中方型凸起的影响比斜坡型凸起的影响更大,模型背面凸起结构对表面脉动压力测量的影响沿着展向逐渐增加.分析认为模型背面凸起结构影响表面脉动压力测量有三种可能途径①模型背面大尺度凸起改变模型流场波系,从而影响模型表面流动;②模型背面非定常流动产生的噪声通过固壁传播至脉动压力传感器,影响测量结果;③模型周围非定常非对称流动给模型施加一个非定常的作用力,使得模型振荡,从而影响表面脉动压力测量.The investigation on transition and turbulence in the hypersonic boundary layer is an attractive region in aerodynamics at present,and the technique of measuring the pressure fluctuation is widely used in the experimental investigation on the background noise of the hypersonic wind tunnel and the development of the disturbing waves in the boundary layer.The measurement from the pressure fluctuation probe could be affected by many factors because of its high sensitivity and wide frequency range.The wedge model was considered as the investigation object and the experiment on the effect of the protuberance the measurements of surface pressure fluctuation was conducted in the conventional hypersonic wind tunnel.The information of surface pressure fluctuation based on three back structures,back such as square protuberance,slope protuberance and none of protuberance,was obtained.It is shown that the noise level remarkably increases in the cases of the square and slope protuberances and the effect of the square protuberance on the noise level was much larger than that of the slop protuberance.Furthermore,the effect of the back protuberances gradually increases in the spanwise direction of the model.Further analyses shows that there are three probable effect mechanism of model protuberance to the pressure fluctuation measurement,firstly,the protuberance on the model back surface change the shock waves,and then affect the flow field on the measurement surface.Secondly,the unsteady flow caused by the protuberance generate aerodynamic noise,the noise propagates to the transducer along the model.Thirdly.the unsteady asymmetric pressure caused by the protuberance make the model vibration,and then affect the pressure fluctuation measurement.

关 键 词：脉动压力 模型凸起 高超声速 非定常流动 噪声 

分 类 号：O354.4[理学—流体力学]