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Air Traffic Control System
Published in Milica Kalić, Slavica Dožić, Danica Babić, Introduction to the Air Transport System, 2022
Milica Kalić, Slavica Dožić, Danica Babić
Wake Vortex Turbulence. Wake vortex, also known as wake turbulence, is defined as turbulence that is generated by the passage of an aircraft in flight. It can arise in several ways, e.g., it will be generated when the nose landing gear of an aircraft lifts off the runway on take-off, as in the case when the nose landing gear touches the ground during landing. However, potentially hazardous wake turbulence of an aircraft in flight is caused by wing tip vortices. Wake vortices are present behind every aircraft, they decompose quite slowly and are most dangerous to the following aircraft for several minutes after they have been generated (ICAO Doc 9426 1984). They are particularly severe when generated by large and wide-bodied jet aircraft.
Force-System Resultants and Equilibrium
Published in Richard C. Dorf, The Engineering Handbook, 2018
Because of the pressure difference between the lower and upper surfaces of a wing, the air tends to “leak” around the wing tips (bottom to top) and produce a swirling flow - the trailing or wing tip vortices shown in Figure 38.8. This swirl interacts with the flow over the entire length of the wing, thereby affecting its lift and drag. The trailing vortices create a flow that makes it appear as though the wing were flying at an angle of attack different from the actual angle. This effect produces additional drag termed the induced drag.
Aerodynamic Forces – Subsonic Flight
Published in Rose G. Davies, Aerodynamics Principles for Air Transport Pilots, 2020
A winglet is a commonly used wing tip device. A winglet can reduce the intensity of wing tip vortex by changing the pressure distribution around wingtip, and reforming the vortex into smaller vortices behind the winglet. The structure of a winglet is relatively simple, and it works effectively. There are varieties of wingtip devices, for example, up-winglet, down-winglet, wing fence, wingtip tank, and so on.
Preliminary investigation on the effects of folding wingtips on the aerodynamics characteristics of flexible aircraft
Published in International Journal of Ambient Energy, 2022
V. Madhan Raj, Dilip A. Shah, P. Boomadevi
Wing is an essential part of aeroplane design. It enables to produce lift for an aeroplane. On commercial aircraft, the main objective is to reduce the drag which is created by the wingtip vortex and increasing the lift. This can be done by using winglets on the tip of the wings. The winglet is a part of a wing which is mainly used to reduce wingtip vortex, induced drag and fuel consumption. The prime objective of this project is by changing the angle of attack the efficiency of the winglet is improved. Reduced the wingtip vortices and induced drag maintains fuel saving up to 6% better lift performance (Whitcomb 1976). To study and analyse the effects of foldable wingtips at a various angle of attack the optimised method from literature is used. Winglet optimisation has great attention, because of its potential to reduce the induced drag. It is a vertical projection on the tip of the wing which reduces wingtip vortices and Induced Drag. Wingtip vortices are formed by the difference in pressure of above and below the wing. It also helps to improve aircraft characteristics and increases the aspect ratio. Accounting 40% of drag during the cruise and 80% of drag during in climb condition is occurring (Guerrero, Maestro, and Bottaro 2012). By reducing drag and fuel consumption thereby increasing lift performance made us to take up this idea. The aim of this project is to carry out the experimental analysis of foldable wingtips. When the aircraft moves in air, wingtip vortices are produced due to its lift generation. To reduce the vortex and by reducing the drag induced on the wing, the lift performance can be enhanced. The fabricated model will be tested in the wind tunnel for lift and drag characteristics (L/D ratio) and force measurement using load cell (Sohaib 2011). The experimental model is made in such a way that the winglet can be foldable up to a certain cant angle. By changing the Cant angle and Angle of attack of the wing and winglet during testing, the experimental data’s can be calculated for lift and drag coefficient using force measurement load cell (Manigandan, Kumar, et al. 2017). Figure 1 represents the winglet with different cant angles. The cant angles are as follows: 90, 180, 150, and 270 degrees.