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metadata.fyp.dc.title: Analysis Of Lift Generated By The Different Angle Of Swept Of A Wing
metadata.fyp.dc.contributor.*: Alif Rashrique Azras Bin Abdul Rasek 18-Sep-2015
metadata.fyp.dc.description.abstract: The purpose of this project mainly is to analysis the lift generated within different swept wing angle in subsonic flight. Wing is the vital part in an aircraft which the function is to produce lift so that the aircraft can fly. There are various types of wings which is swept wing, delta wing, and straight wing. Each type of wing are used depend on what the aircraft serve. The wingspan or wing length of an aircraft is measured from one wingtip to wingtip. It is always being measured in a straight line despite what the wing shape is. In the designing work of the aircraft wing, the CATIA software is used so that all measurement and detail can be precisely produce. After that, it is then to be tested in the XFlow software to analyse the lift generate at the wing. For this project, different angle of swept were chosen to see the affect it gives to the generation of lift. The airfoil type that has been chosen for this research was taken from the Boeing 737 that is (b737a-il), (b737b-il), (b737c-il) and (b737d-il) and a slight modification was done to adjust its swept angle. The analyse and evaluate the data that has been collected from reading sources and the analysis from the software itself. After the data analysing process is done, the results are presented in the form of screenshots, figures and graphs. The results shows that, the wing with the 25o angle of swept is the most efficient in term of coefficient of lift to drag ratio (CL/CD). Nevertheless, the results of the simulation can be compared with the wind tunnel result to verify the validity of the result from the simulation.
metadata.fyp.dc.description: Bachelor of Aircraft Engineering Technology – Mechanical December 2014
metadata.fyp.dc.identifier.uri: http://localhost/xmlui/handle/123456789/10925
Appears in Collections:Final Year Project - UniKL MIAT

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