Abstract
Objectives: The objective of this work is to investigate the flow over the truncated NACA2414 airfoil with slotted flap configuration. Investigation is carried using wind tunnel and commercial CFD tools with the consequences of the variation of speed, angle of attack of control surface and effective angle of attack. Methods/Statistical Analysis: Wind tunnel tests are performed on a reduced scale model (3:10) in wind tunnel at Manipal University. Experimentally determined static pressure distribution data at equal interval stations, placed over the wing are used to generate pressure data. The results obtained are used in turn as a benchmark to validate the CFD simulations. Findings: Findings clearly states that the blunt trailing edge has high drag coefficient. Although off set cavity and cavity has proven to be the ideal modification for trailing edge shape in a plane wing from the study. It can be concluded that the same is not true when such modifications are applied to slotted flap configuration. Application/Improvements: Further studies can be carried out with the alternative designs and a rigorous research can contribute in efficient designs in high lift devices. Keywords: High-lift Devices, Numerical Analysis, Slotted Flaps, Truncated Airfoil, Wind Tunnel
Highlights
Optimization of the aircraft performance has been the motivation behind the ever-expanding aircraft industry
With increment in trailing edge angle of attack the lift has increased till 11 degree with increment in further angle result has varied by the flow induced vortices which has influenced the cavity section resulting in the low lift coefficient
It clearly states that the blunt trailing edge has high drag at low angle of attack, which has reached to minimal point at angle of 4 degree in further increment the coefficient of drag has increased
Summary
Optimization of the aircraft performance has been the motivation behind the ever-expanding aircraft industry. Slightest of the design improvements has the potential to boost the performance of the aircrafts in the long run. The Slotted flaps design has been used to increase the lift coefficient of the primary wing to a considerable extent. Any geometrical variation in the trailing edge of an airfoil implies a considerable change in lift and drag characteristics of the airfoil[1]. This change in the lift characteristics are the byproducts of eddies formed at the end of the trailing edge of the airfoil. Different shapes for the trailing edges are considered to study the effectiveness of the designs
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