Performance Testing of NACA0012 Aerofoil by Providing Dimple Surface

Abstract

The aim of research paper is to delay the flow separation of an aerofoil by providing dimples on the upper surface of aerofoil at trailing edge. In present work research is done on experimental and numerical analysis of lift and drag performance of NACA0012 aerofoil. The lift and drag forces are calculated at different angle of attack varying from 00to 200 for low Reynolds number. The flow characteristics over NACA0012 aerofoil are studied experimentally in a low speed wind tunnel. All the models are prepared by wood and experiments are conducted in 300mm x 300mm x 1000mm subsonic wind tunnel. Lift and Drag coefficient were calculated and obtained results were plotted against angle of attack. From the experimental investigation has been observed that the flow separation of aerofoil can be delayed by using dimples on the upper surface. That indicates by providing dimple surface we can able to control flow separation successfully.

Authors and Affiliations

Prathmesh Bhogle, Aniket Padalkar, Suraj Takke, Manish Yedge, Sandesh Rasal

Keywords

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  • EP ID EP23935
  • DOI http://doi.org/10.22214/ijraset.2017.4229
  • Views 263
  • Downloads 9

How To Cite

Prathmesh Bhogle, Aniket Padalkar, Suraj Takke, Manish Yedge, Sandesh Rasal (2017). Performance Testing of NACA0012 Aerofoil by Providing Dimple Surface. International Journal for Research in Applied Science and Engineering Technology (IJRASET), 5(4), -. https://europub.co.uk/articles/-A-23935