跨声速流场扰动模态与湍流度精细测量

doi:10.7527/S1000-6893.2021.26378

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跨声速流场扰动模态与湍流度精细测量

朱博¹,廖达雄²,陈振华²,陈吉明¹

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
2. 中国空气动力研究与发展中心

收稿日期:2021-09-14 修回日期:2021-11-21 出版日期:2021-11-23 发布日期:2021-11-23
通讯作者: 朱博
基金资助:
空气动力学国家重点实验室基金

A fine measurement for fluctuations mode and turbulence level in transonic flow

Received:2021-09-14 Revised:2021-11-21 Online:2021-11-23 Published:2021-11-23
Contact: Bo ZHU
Supported by:
State Key Laboratory of Aerodynamics Foundation

摘要/Abstract

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。

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

Abstract: 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.

Key words: compressible flow, fluctuations mode, turbulence level, hot wire anemometer, transonic wind tunnel, con-tinuous wind tunnel

中图分类号:

朱博廖达雄陈振华陈吉明. 跨声速流场扰动模态与湍流度精细测量[J]. 航空学报, doi: 10.7527/S1000-6893.2021.26378.

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

跨声速流场扰动模态与湍流度精细测量

A fine measurement for fluctuations mode and turbulence level in transonic flow

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