ABSTRACT
Investigation of effects of Dimples on NACA 0018
Airfoil using CFD
This study focuses on the application of dimples on an airfoil to enhance
aerodynamic characteristics, particularly targeting drag reduction and stall
mitigation. Dimpled surfaces are known to generate swirl by creation of vortices
there by energizing the flow. It is believed that the generation of vortices and swirl
can be used to delay the boundary layer separation thus improving Lift, reducing
drag and delaying stall for an Airfoil. The primary objective is to delay flow
separation at the stall point, thereby improving maneuverability and overall aircraft
performance. Computational Fluid Dynamics (CFD) analysis is conducted on a
symmetrical NACA0018 airfoil which will reduce the drag and delay the flow
separation point over the upper surface of an airfoil by using dimple effect. The
analysis is carried out with inlet velocity of 30m/s at different Angle of attack
(0,4,8,12,16). The comparison of parameters such as Co-efficient of Lift, Coefficient of Drag, L/D ratio, Velocity contours, Pressure contours and Turbulent
kinetic energy contours are performed in between the Plain airfoil, Dimpled airfoil
inwards and a dimpled airfoil outwards. This research contributes valuable insights
into utilizing dimples for optimizing airfoil performance.
B. Yethin Pushpa Raj
(22N31A2104)
D. Raj Kumar Bhargav
(23N35A2103)
M. Dilip
(23N35A2109)
P. Sirisha
(23N35A2111)
Signature of the supervisor
Signature of the project Co-ordinator