Keywords : Reduction in Stall

Performance Improvement of Subsonic aircraft wing by Dimple Effect

Sivaraman S; Ganesh M; Saravanan R; Saravana kumar

International Research Journal on Advanced Science Hub, 2021, Volume 3, Issue Special Issue ICARD-2021 3S, Pages 195-199
DOI: 10.47392/irjash.2021.091

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.

Numerical Analysis of Dimple Effect on Airfoils for varied AoA

Saravanan R; Sharu Sri K; Sundareswaran E; Vyshnavi Krishnamoorthy; Sri Balaji S

International Research Journal on Advanced Science Hub, 2020, Volume 2, Issue Special Issue ICAMET 10S, Pages 86-94
DOI: 10.47392/irjash.2020.204

The main objective of aircraft aerodynamics is to enhance the aerodynamic characteristics and manoeuvrability of the aircraft. This enhancement includes the reduction in drag and stall phenomenon. The airfoil, which contains dimples, will have comparatively less drag than the plain airfoil. Introducing dimples on the aircraft wing will create turbulence by creating vortices, which delays the boundary layer separation resulting in decrease of pressure drag and increase in the angle of stall. In addition, wake reduction leads to reduction in acoustic emission. The overall objective of this study is to improve the aircraft manoeuvrability by delaying the flow separation point at stall and thereby reducing the drag by applying the dimple effect over the aircraft wing. This Study includes computational analysis of dimple effect on NACA 0018 airfoil. Dimple shapes of square selected for the analysis; airfoil tested under the inlet velocity of 30m/s at different angle of attack (12˚, 14˚, 16˚, 18˚,) for 8mm & 10mm diameter of Dimples. This analysis favours the dimple effect by increasing L/D ratio and thereby providing the maximum aerodynamic efficiency, which provides the enhanced performance for the aircraft