Abstract
Aerodynamic performance of aircraft wings vary with flight path conditions and depend on efficiency of high lift systems. In this work, a study on high lift devices and mechanisms that aim to increase maximum lift coefficient and reduce drag on commercial aircraft wings is discussed. Typically, such extensions are provided to main airfoil along span wise direction of wing and can increase lift coefficient by more than 100% during operation. Increasing the no of trailing edge flaps in chord wise direction could result in 100% increment in lift coefficient at a given angle of attack but leading edge slats improve lift by delaying the flow separation near stall angle of attack. Different combinations of trailing edge flaps used by Airbus, Boeing and McDonnel Douglas manufacturers are explained along with kinematic mechanisms to deploy them. The surface pressure distribution for 30P30N airfoil is evaluated using 2D vortex panel method and effects of chord wise boundary layer flow transitions on aerodynamic lift generation is discussed. The results showed better agreements with experiment data for high Reynolds number (9 million) flow conditions near stall angle of attack.
Highlights
Slats and flaps are high lift devices, intended to produce maximum lift coefficients on aerodynamically designed surfaces as found on aircraft wings, helicopter blades
Aircraft wing design in terms of the leading edge devices viz slats, Kruger flaps combined with single-and double-slotted Fowler flaps at trailing edge are predominant high-lift devices of choice
The inboard wing of aircraft is usually equipped with a droop nose device during a takeoff or landing operation, since it offers good aerodynamic performance compared to sealed leading-edge slat
Summary
Slats and flaps are high lift devices, intended to produce maximum lift coefficients on aerodynamically designed surfaces as found on aircraft wings, helicopter blades. Computational study by Xuguo et al (2009), Deng et al (2018) has shown the effects of ground height distance to airfoil on the lift, drag and nose up or nose down pitching moments of an aircraft for two different airfoil configurations. The primary significance and objective of high lift devices on aircraft wings presents a discussion about lift improvement methodologies through use of slots on leading and trailing edge regions of airfoil. Maximum lift coefficients achieved for different types of high lift configurations on commercial aircraft wings are discussed as well as role of the kinematic mechanisms. Conclusions and an overview of the future work is presented
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