Abstract
In this study, surface features such as dimples and bumps are introduced to the surface of a NACA 0012 airfoil to study their effect on boundary layer separation, particularly at high angles of attack. Six modified airfoils were designed with dimples and bumps of spherical and pyramidical shapes. A computational fluid dynamics (CFD) analysis was conducted on these models at subsonic flow using Ansys Fluent. The analysis used the Shear Stress Transport k – ω turbulence model at a varying angle of attack (AOA) from 0 to 15°. The velocity contours and streamlines were generated. Also, the lift coefficient, drag coefficient and the lift-to-drag performance ratio were computed and analyzed. The results showed that all surface modifications led to delayed flow separation and flow recirculation. All surface modification also resulted in a decrease in drag at 15°. All designs, except pyramidical protrusions, increased the lift-to-drag ratio (L/D) performance at 15°. It was found that dimples are better than bumps and spherical features are better than pyramidical ones.
Highlights
The aviation industry today is the safest and most efficient it has been since the first aircraft was invented
And 21, there is a significant improvement in the boundary layer separation from the clean airfoil. This improvement is accompanied with an improvement in the lift-to-drag ratio (L/D) performance
The aim of this study was to understand the airflow around an airfoil and how the introduction of surface features like dimples and bumps affect the flow
Summary
The aviation industry today is the safest and most efficient it has been since the first aircraft was invented. A new area of interest is the study of texture on an aircraft wings. These textures, which can be raised or depressed, have shown to induce local vortices. These vortices increase the momentum of the boundary layer and decrease pressure drag. These conditions lead to a delay in boundary layer separation at higher angles of attack (AOA) and, increase the stall angle. Stall is a highly unfavorable phenomenon that reduces an aircraft performance and safety. Reducing the pressure drag is of great interest as it reduces fuel consumption, increases safety, and improves the overall performance of an aircraft
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