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PIV MEASUREMENTS OF THE NEAR-WAKE FLOW OF AN AIRFOIL ABOVE A FREE SURFACE
Authors:Daichin  KANG Wen  ZHAO Li-li
Affiliation:1. Shanghai Institute of Applied Mathematics and Mechanics, Shanghai University, Shanghai 200072, China;2. Rapid Manufacturing Engineering Center, Shanghai University, Shanghai 200444, China;1. Theoretical Physics Department, CERN, CH-1211 Genève 23, Switzerland;2. Faculty of Science and Technology, University of Stavanger, 4036 Stavanger, Norway;1. ASTUTE, Engineering Central, Swansea University Bay Campus, SA1 8EN, UK;2. ProHeat, Conwy House, Tawe Business Village, Swansea Enterprise Park, SA7 9LA, UK;1. Tohoku University, 2-1-1 Katahira, Aoba-ku, 980-8577 Sendai, Japan;2. Special Materials Corp., 28A Bolshoy Sampsonievsky Ave., 194044 Saint Petersburg, Russia;3. Peter the Great Saint Petersburg Polytechnic University, 29 Polytechnicheskaya Str., 195251 Saint Petersburg, Russia;1. Department of Mechanical and Mechatronic Engineering, National Taiwan Ocean University, Keelung 202, Taiwan, ROC;2. Department of Aeronautics and Astronautics, R.O.C. Air Force Academy, Kaohsiung 820, Taiwan, ROC;1. Department of Mechanical Engineering, National Taiwan University of Science and Technology, Taipei 10672, Taiwan, Republic of China;2. Department of Mechanical Design Engineering, National Formosa University, Yunlin County 63246, Taiwan, Republic of China
Abstract: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 3.5×103. 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.
Keywords:wing-in-ground effect  NACA0012 airfoil  free surface  wake flow  Particle Image Velocimetry (PIV) measurement
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