一种翼型风洞试验数据的不确定度分析方法  

An Uncertainty Analysis Method for Wind Tunnel Tests Data of Airfoil

作　　者：张翼行 高超[1] 严日华 张正科[1] 武斌[1] Yi-xing Zhang;Chao Gao;Ri-hua Yan;Zheng-ke Zhang;Bin Wu(National Key Laboratory of Science and Technology on Aerodynamic Design and Research,Northwestern Polytechnical University)

机构地区：[1]翼型叶栅空气动力学国防科技重点实验室,西北工业大学

出　　处：《风机技术》2023年第6期41-47,53,共8页Chinese Journal of Turbomachinery

基　　金：国家自然科学基金项目(12172299,1190021162)。

摘　　要：对风力机翼型进行气动分析、优化设计以及风洞试验研究等工作,对提高叶片的风能捕获能力、减小叶片的质量和相应的系统载荷具有重要的意义。风洞试验数据分析是试验研究的重要环节,试验数据的不确定度分析对试验结果的可靠性有着重要的影响。风洞试验是一个多环节的复杂过程,如何有效地分析各类误差源的影响对获取真实可靠的风洞试验数据至关重要。本文给出了一种翼型风洞试验数据不确定度的分析方法,运用该方法对OA309标准模型翼型在马赫数0.4,0.8时,风洞试验得到的升力系数,阻力系数,俯仰力矩系数不确定度进行了分析,得到了实验误差范围,通过对结果进行分析发现:压力传感器的准确度对试验结果影响较大。Ma=0.4时,升力系数的不确定度相对自身而言较小,仅为1.4%,阻力系数的不确定度相对自身而言较大,最大为8.1%,俯仰力矩系数的不确定度为6.41%。The aerodynamic analysis and optimization design of high-performance wind turbine wing shapes,as well as wind tunnel experimental research,are of great significance for improving the wind energy capture ability of blades,reducing the weight of blades,and corresponding system loads.The analysis of wind tunnel test data is an important part of experimental research,and the uncertainty analysis of test data has a significant impact on the reliability of test results.Wind tunnel experiment is a complex process with multiple links.How to effectively analyze the influence of various error sources is the most important issue in getting reliable wind tunnel experiment datas.In this paper,an uncertainty analysis method for airfoil wind tunnel tests data is given.The uncertainty of lift coefficient,drag coefficient and pitching moment coefficient obtained from tests of OA309 airfoil at Ma=0.4 and Ma=0.8 is analyzed by using this method,and the range of test errors caused by various error sources are obtained.Through the analysis of the results,it is found that the accuracy of the pressure sensor has a greater impact on the test results;the uncertainty of the lift coefficient is relatively small,only 1.4%;the maximum of the uncertainty of the drag coefficient is 8.1%;the uncertainty of pitching moment coefficient is 6.41%.

关 键 词：风洞试验 不确定度 偏离极限 精度极限 

分 类 号：V217[航空宇航科学与技术—航空宇航推进理论与工程]