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三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，通过实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1.5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0.2～1.5流场测量实验，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。
Research on fine measurement for compressible flow fluctuations mode and turbulence level in transonic wind tunnel is carried out to satisfy the need of low turbulence flow test for high speed aircraft. Based on the measurement of var-ying hot wire overheat ratio, functions of the general mode and three special modes including vorticity mode, entropy mode and acoustic mode for transonic flow fluctuations were derived. According to this method, an experiment was carried out, fluctuations diagrams of general mode, vorticity mode and acoustic mode were obtained, high accuracy turbulence level was calculated, fluctuations diagram analysis in frequency domain was used for rationalizing flow mechanism at Ma 1.5, and a measurement method for fluctuations mode and low turbulence level was built. When the Mach number varied from 0.2 to 1.5 in the new type continuous transonic wind tunnel, the turbulence level was around 0.037%～0.197%, nonlinear function fitness goodness of data was around 0.943～0.995, Monte Carlo simu-lation uncertainty was around 0.0002%～0.0041%. Research results show that the method of fluctuations mode and low turbulence level measurement is effective, which is practical for flow field quality evaluation and optimization, and low turbulence test of high speed aircraft in high-performance transonic wind tunnel.
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