Design, Analysis, Prototyping and Testing of Aerofoils for High-Lift at Low Reynolds Number

Abstract

Increased payloads, reduced aircraft noise, shortened takeoff and landing distances and lowered stall speeds can all be achieved from the direct effects of improved high-lift aerofoil aerodynamics. It is, therefore, not surprising that the high-lift aerofoil design has been and will remain a topic of interest. Along with the interest, the opportunity is to make it more cost-effective. One possible way to achieve the objective is to build a cheaper yet simpler high-lift system. This presents a challenge to the high-lift aerodynamicist: to design a less complex flap that maintains high-lift and meanwhile lowers the flow separation. Furthermore, by designing the high-lift system to achieve longer attachment of flow onto the flap, aircraft noise will be reduced. This research article presents the design, analysis and prototyping and testing of aerofoil which was carried out after performing a literature survey on the performance of many aerofoils at low Reynolds number. This research was achieved using Vortex generators for high lifts. The prototype was tested in the wind tunnel.