跨声速风洞中的超临界翼型速度场测量  

Velocity Field Measurement of Supercritical Airfoil in Transonic Wind Tunnel

作　　者：王猛[1] 李玉军[1] 衷洪杰[1] 

机构地区：[1]中航工业空气动力研究院高速高雷诺数航空科技重点实验室,辽宁沈阳110034

出　　处：《航空科学技术》2015年第8期73-78,共6页Aeronautical Science & Technology

基　　金：航空科学基金(2011ZD26001)~~

摘　　要：针对跨声速风洞实验环境，发展适用于高速流动测量的粒子图像测速（PIV）实验技术，从而实现对超临界翼型的非定常流动进行准确的速度场测量。对跨声速风洞中的PIV测量系统进行了如下改进工作：改进粒子播撒装置；对片光光路布局进行了优化；对模型表面进行了防漫反射处理；提高图像位移场计算精度。使用RAE 2822超临界翼型，在FL-1风洞进行实验，来流马赫数为0.6-0.92，雷诺数为1.86×10^6-2.58×10^6。结果表明，利用PIV测得的速度场能够有效捕捉激波位置，并且与表面平均压力分布一致，通过对PIV数据进行统计分析可得到激波振荡的类型及幅度等特征。A PIV measurement system had been developed to measure the unsteady flow structure of the supercritical airfoil in transonic wind tunnel. The following improvements had been made to the PIV measurement system for transonic wind tunnel： improved particle seeding device, optimized the light path arrangement, anti-diffuse reflection treatment on the model surface, and increased the image displacement field calculation accuracy. An experiment was conducted at FL-1 wind tunnel to investigate the behavior of transient shock wave/boundary layer interaction on a supercritical airfoil （RAE 2822）. The Mach number was between 0.6 and 0.92, and Reynolds number between 1.86×10^6 and 2.58×10^6. The results show that the velocity field measured by PIV can effectively capture the shock position, and the average pressure distribution is consistent with that of the PIV data. The type and magnitude of the shock wave can be obtained by statistical analysis.

关 键 词：跨声速 风洞 超临界翼型 速度场 粒子图像测速 激波 边界层 激波-边界层干扰 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]