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Kimey Wazare
Kimey Wazare • Mar 31, 2016

Performance Analysis of Winglet at various Angle of Attack.

Project Abstract / Summary : Wing is an important and integral part of the aircraft body, which gives the sufficient lift and drag forces for take-off, landing and at high altitudes. Wingspan has certain limit over a capacity and those can be overcome with an extension at wing tip known as WINGLET, which helps to augment required lift and reduce induced drag caused by wingtip vortices. Various studies shows that the aerodynamics performance of a subsonic aircraft having blended winglet at specific cant angle. But this study mainly includes analysis of elliptical winglet at various cant angles 30, 45, 60, & 90 degree by varying angle of attack. The design has NACA 23015 for wing root, NACA 23012 for wing tip and winglet with elliptical shape. CAD modelling done in CATIA V5 R21, Meshing & Simulations are carried out in ANSYS 16. Flow features of entire wing and winglet were examined in wind tunnel test.
The Study mainly highlights the shape of winglet by varying the cant angle at different angle of attacks. The project is totally based on charetered planes wingspan only, as it is too small comparative with jet planes. We have taken Beech craft King air 350Er as reference plane, for that winglet are extended section of wing airfoil with blended type, but we are going to introduce elliptical winlet means airfoil is limited only uptill wingtip, from it shape correspondingly changes. Its said that elliptical winglet reduces more amount of induced drag comparative different types of winglet shapes. But only changing shape don't show greater impact on reducing total drag, its mandatory to change the cant angles. Angle of attack plays a very crucial role in generating lift and drag force. So if we tested are geometry of wing & winglet with different cant angles even by varying angle of attack.

Why did you choose to work on this project topic : In aerospace industry, there is need of generating more lift force and reduce the induced drag. So for that winglet came into existence, but that too with specific cant angles. So just an idea strike in the head why can't we vary cant angles with respect to various angle of attack. After a long term literature review we finalized this topic.
Future scope: Aerospace industry can implement the winglet section at various cant angles.

Project Highlights : As this project will lead aerospace industry, in achieving their long term goal of increasing the lift force and parallely reducing induced drag. Winglet sections can be modified, even sectional area, cant angles and many more. So we all think we can win this contest.


Project Category : Mechanical / Automobile / Aeronautical
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Institute/College Name: ZES's Zeal College of Engineering And Research, Narhe
City: Pune
State: Maharashtra
Participating Team From: Final Year

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