Performance Improvement of Subsonic aircraft wing by Dimple Effect

Authors

  • Sivaraman S ssistant Professor, Dept. of Aeronautical Engineering, Hindusthan College of engineering and technology, Coimbatore, Tamilnadu, India. Author
  • Dr Ganesh M Assistant Professor, Dept. of Aeronautical Engineering, Hindusthan College of engineering and technology, Coimbatore, Tamilnadu, India Author
  • Saravanan R Assistant Professor, Dept. of Aeronautical Engineering, Hindusthan College of engineering and technology, Coimbatore, Tamilnadu, India. Author
  • Saravanakumar Assistant Professor, Dept. of Aeronautical Engineering, Hindusthan College of engineering and technology, Coimbatore, Tamilnadu, India. Author

DOI:

https://doi.org/10.47392/irjash.2021.091

Keywords:

Aerofoil, Effect of Dimple, Separation of Flow, Reduction in Stall, the Boundary layer

Abstract

Improving lift and drag ratio is the most important parameter that helps to improving the aerodynamic efficiency of the wing Vortex generators are used to delay flow separators for higher angle of attacks. Simple on surface of body tend provide vortex to delay flow separators and make boundary layer attached with the surface. NACA 0018 symmetrical aerofoil is considered for analysis of dimple in various position on the wing like leading edge, middle of the wing and end of the wing to predict optimum position. In that dimple in middle of the wing shows good improvement in delaying the flow separation this improves the lift to drag ratio compared to other position of the wing.

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Published

2021-03-01

Issue

Vol. 3 No. 3S (2021): IRJASH Vol.03 (Special Issue ICARD 3S) Issue 3S-[MAR 2021]

Section

Research Articles

License

Creative Commons License

This work is licensed under a Creative Commons Attribution-NonCommercial 4.0 International License.