PIV MEASUREMENTS OF THE NEAR-WAKE FLOW OF AN AIRFOIL ABOVE A FREE SURFACE  

作　　者：Daichin KANG Wen ZHAO Li-li 

机构地区：[1]Shanghai Institute of Applied Mathematics and Mechanics, Shanghai University, Shanghai 200072, China [2]Rapid Manufacturing Engineering Center, Shanghai University, Shanghai 200444, China

出　　处：《Journal of Hydrodynamics》2007年第4期482-487,共6页水动力学研究与进展B辑（英文版）

基　　金：the National Natural Science Foundation of China (Grant No.10572082);the Shanghai Leading Academic Discipline Project (Grant No.Y0103).

摘　　要：The near-wake flow of a NACA0012 airfoils mounted above a water surface were experimentally studied in a wind/wave tunnel. The main objective of this study is to investigate the influence of the free surface on the structure of the airfoil trailing wake. The flow structure was measured with different ride heights between the airfoil and free surface using a Particle Image Velocimetry （PIV） system. The Reynolds number based on the chord length of the airfoil was about 3.5×10^3. For each experimental condition, large amount of instantaneous velocity fields were captured and ensemble-averaged to get the spatial distributions of mean velocity and mean vorticity, as well as turbulence statistics. The results show that the flow structures of the airfoil wake varies remarkably with the change in the ride height.The near-wake flow of a NACA0012 airfoils mounted above a water surface were experimentally studied in a wind/wave tunnel. The main objective of this study is to investigate the influence of the free surface on the structure of the airfoil trailing wake. The flow structure was measured with different ride heights between the airfoil and free surface using a Particle Image Velocimetry （PIV） system. The Reynolds number based on the chord length of the airfoil was about 3.5×10^3. For each experimental condition, large amount of instantaneous velocity fields were captured and ensemble-averaged to get the spatial distributions of mean velocity and mean vorticity, as well as turbulence statistics. The results show that the flow structures of the airfoil wake varies remarkably with the change in the ride height.

关 键 词：wing-in-ground effect NACA0012 airfoil free surface wake flow Particle Image Velocimetry （PIV） measurement 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]