This research focused on investigating flow control using surface roughness along the leading edge of an airfoil. The current design will entail a system that can accurately predict flow separation on the upper surface. This is done by measuring the angle of attack and static pressure to determine flow separation. For future research this can
The objective of this project is to determine if altering a standard wing with tear-drop shaped pimples can reduce the effects of drag without utilizing expensive technology. To test this an airfoil based on a standard National Advisory Committee for Aeronautics 0012 model airfoil was designed with the tear-drop pimples and tested using a wind-tunnel,
The objective for this research was to model the effects of a wing with leading-edge roughness device’s on coefficient of lift and drag when at high angles of attack near stall, the addition of which potentially increases the stall angle and reduces stall speed. This research was conducted using Computational Fluid Dynamics, modeling an airfoil
Reducing the drag on an airfoil through new designs will lead to better aircraft fuel efficiency.
Investigating the effect of an aircraft wing’s surface roughness will lead to decreased fuel consumption.
Analyzing the effect of aircraft surface roughness will inform engineers of ways to increase lift capacity and efficiency.