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Numerical Analysis of Effect of Leading-Edge Rotating Cylinder on NACA0021 Symmetric Airfoil

Author

Listed:
  • Md. Abdus Salam

    (Department of Aeronautical Engineering (AE) in Military Institute of Science and Technology, Mirpur Cantonment, Dhaka, Bangladesh)

  • Vikram Deshpande

    (Department of Aeronautical Engineering (AE) in Military Institute of Science and Technology, Mirpur Cantonment, Dhaka, Bangladesh)

  • Nafiz Ahmed Khan

    (Department of Aeronautical Engineering (AE) in Military Institute of Science and Technology, Mirpur Cantonment, Dhaka, Bangladesh)

  • M. A. Taher Ali

    (Department of Aeronautical Engineering (AE) in Military Institute of Science and Technology, Mirpur Cantonment, Dhaka, Bangladesh)

Abstract

The moving surface boundary control (MSBC) has been a Centre stage study for last 2-3 decades. The preliminary aim of the study was to ascertain whether the concept can improve the airfoil characteristics. Number of experimental and numerical studies pointed out that the MSBC can superiorly enhance the airfoil performance albeit for higher velocity ratios (i.e. cylinder tangential velocity to free stream velocity). Although abundant research has been undertaken in this area on different airfoil performances but no attempt was seen to study effect of MSBC on NACA0021 airfoil for and also effects of lower velocity ratios. Thus, present paper focusses on numerical study of modified NACA 0021 airfoil with leading edge rotating cylinder for velocity ratios (i.e.) between 1 to 1.78 at different angles of attack. The numerical study indicates that the modified airfoil possess better aerodynamic performance than the base airfoil even at lower velocity ratios (i.e. for velocity ratios 0.356 and beyond). The study also focusses on reason for improvement in aerodynamic performance by close look at various parameters.

Suggested Citation

  • Md. Abdus Salam & Vikram Deshpande & Nafiz Ahmed Khan & M. A. Taher Ali, 2019. "Numerical Analysis of Effect of Leading-Edge Rotating Cylinder on NACA0021 Symmetric Airfoil," European Journal of Engineering and Technology Research, European Open Science, vol. 4(7), pages 11-17, July.
    • Handle: RePEc:epw:ejeng0:v:4:y:2019:i:7:id:61385
    DOI: 10.24018/ejeng.2019.4.7.1385
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