Analyzing The Synergistic Effects of Geometric Surface Modifications through Dimples at 35% of the chord from the leading edge And Static Extended Trailing Edge on NACA 0012 Aerofoil

  Sanjida Sharmin,  Joy Barman Sagar,  Sourav Paul,  Shaswato Barua,  Arnab Dutta

Dimples on aerofoil cause flow separation delay which results in improved lift coefficient (CL) and decreased drag coefficient (CD). Flaps at different angles also serve the same purposes. The combined effect of these two on aerofoil is a new area of research in aerodynamics. In this work, the combined effect of flaps and dimples have been studied on NACA0012 aerofoil through computational fluid dynamics (CFD) where k- ω shear stress transport (SST) turbulence model has been applied. The semicircular dimple of diameter 0.05 m is positioned at 35% of the chord from the leading edge. 2D simulations are done with the combination of four angles of attack (AoA) (0º, 4º, 8º, 12º) and five flap angles (0º, 5º, 10º, 15º, 20º). The Inlet velocity condition is set to be 60 m/s along the x-direction. The findings favor the 15º degree flap model to be the best performance-efficient model and suggest 4 º AoA as the best suitable position to operate for all models regarding lift to drag ratio (L/D).

Keywords- Aerofoil, Dimples, Flaps, AoA, CL and CD.

Unique Identification Number - IJEDR2101001
Page Number(s) - 1-7
Pubished in - Volume 9 | Issue 1 | January 2021
DOI (Digital Object Identifier) -    http://doi.one/10.1729/Journal.25624
Publisher - IJEDR (ISSN - 2321-9939)

  Sanjida Sharmin,  Joy Barman Sagar,  Sourav Paul,  Shaswato Barua,  Arnab Dutta,   "Analyzing The Synergistic Effects of Geometric Surface Modifications through Dimples at 35% of the chord from the leading edge And Static Extended Trailing Edge on NACA 0012 Aerofoil", International Journal of Engineering Development and Research (IJEDR), ISSN:2321-9939, Volume.9, Issue 1, pp.1-7, January 2021, Available at :http://www.ijedr.org/papers/IJEDR2101001.pdf