定/变热线过热比跨超声速流场湍流度测量

朱博; 熊波; 吴巍; 王宁

doi:10.13224/j.cnki.jasp.20210575

定/变热线过热比跨超声速流场湍流度测量

doi: 10.13224/j.cnki.jasp.20210575

朱博^1,,
熊波²,
吴巍¹,
王宁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，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

基金项目:

空气动力学国家重点实验室基金 JBKY15040501

详细信息

作者简介:
朱博（1973-），男，高级工程师，硕士，主要从事风洞流场湍流测试与分析。E⁃mail：bobjou@139.com

中图分类号: V211.7
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出版历程
- 收稿日期: 2021-10-12

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

1.
Facility Design and Instrumentation Institute，China Aerodynamics Research and Development Center，Mianyang Sichuan 621000，China
2.
High Speed Aerodynamics Institute，China Aerodynamics Research and Development Center，Mianyang Sichuan 621000，China

摘要

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。
- 跨超声速流 /
- 湍流度 /
- 热线风速仪 /
- 暂冲式风洞 /
- 流场校测
Abstract:
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.
- transonic and supersonic flow /
- turbulence level /
- hot wire anemometry /
- blow down wind tunnel /
- flow field calibration
注释:

1) 张雪

HTML

图 1 风洞实验布置图

Figure 1. Arrangement diagram for test in the wind tunnel

下载: 全尺寸图片幻灯片

图 2 热线过热比为0.8的Ma=2流场热线电压频谱图

Figure 2. Hot wire voltage spectrum of overheat 0.8 at Ma=2

下载: 全尺寸图片幻灯片

图 3 变八过热比的Ma=0.40~2.00流场扰动模态图

Figure 3. Flow fluctuation diagrams of eight overheat ratio measurement at Ma=0.40~2.00

下载: 全尺寸图片幻灯片

图 4 流场变二过热比测量结果（Ma=0.3~4.25）

Figure 4. Results of two overheat ratio measurement （Ma=0.3~4.25）

下载: 全尺寸图片幻灯片

图 5 流场湍流度3种测量方法比较（Ma=0.40~2.00）

Figure 5. Turbulence level comparison between three measurement methods （Ma=0.40~2.00）

下载: 全尺寸图片幻灯片

图 6 流场湍流度两种测量方法比较（Ma=0.30~4.25）

Figure 6. Turbulence level comparison between two measurement methods （Ma=0.30~4.25）

下载: 全尺寸图片幻灯片

表 1 变八过热比的流场脉动量测量结果

Table 1. Measured results of eight overheat ratio measurement for the flow fluctuation

实验段速度马赫数	流量脉动 $〈m〉$ /%	总温脉动 $T_{0}$ /%	相关系数 $R_{m T 0}$	密度脉动 $〈ρ〉$ /%	湍流度 $〈u〉$ /%	非线性方程拟合优度	不确定度/%
0.40	0.136	0.030	0.131	0.008	0.128	0.953	0.003
0.70	0.229	0.082	0.960	0.038	0.191	0.903	0.017
0.80	0.647	0.202	0.960	0.132	0.515	0.937	0.008
0.95	1.274	0.174	1.003	0.339	0.935	0.963	0.033
1.50	0.178	0.101	0.843	0.085	0.093	0.962	0.002
2.00	0.169	0.051	0.455	0.104	0.065	0.965	0.001

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