The computational study on the aerodynamic characteristics of airfoils using fluent / Zulkifli Yahaya

Steady-state, two-dimensional CFD calculations were made for the symmetry airfoil, NACA 0012 and cambered airfoil, WORTMANN FX 63-137 using the standard turbulence model, K-B model of commercial code, FLUENT. Comparisons of aerodynamics characteristics, pressure contours, and velocity vectors were m...

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التفاصيل البيبلوغرافية
المؤلف الرئيسي:	Yahaya, Zulkifli
التنسيق:	أطروحة
اللغة:	English
منشور في:	2005
الموضوعات:	TL Motor vehicles Aeronautics Astronautics
الوصول للمادة أونلاين:	https://ir.uitm.edu.my/id/eprint/76929/1/76929.pdf
الوسوم:	إضافة وسم لا توجد وسوم, كن أول من يضع وسما على هذه التسجيلة!

id	my-uitm-ir.76929
record_format	uketd_dc
spelling	my-uitm-ir.769292023-11-07T09:20:02Z The computational study on the aerodynamic characteristics of airfoils using fluent / Zulkifli Yahaya 2005 Yahaya, Zulkifli TL Motor vehicles. Aeronautics. Astronautics Steady-state, two-dimensional CFD calculations were made for the symmetry airfoil, NACA 0012 and cambered airfoil, WORTMANN FX 63-137 using the standard turbulence model, K-B model of commercial code, FLUENT. Comparisons of aerodynamics characteristics, pressure contours, and velocity vectors were made between the two airfoils. The effects of Reynolds numbers, angles of attack, and airfoil profiles on the airfoils were investigated. Results showed that for each and increased Reynolds number with corresponding angle of attack, the cambered airfoil has increasing and higher values of CL and Co than the symmetry airfoil. As the Reynolds number and the angle of attack are increased, the stagnation points of both airfoils are moved further backward to the lower surface. The cambered airfoil, WORTMANN FX 63-137, has clear pressure difference between the upper and the lower surfaces. The lower surfaces have higher pressure than upper surface. The highest pressure is at the leading edge, followed by the pressure at trailing edge. For symmetry airfoil, NACA 0012, 'ihe upper surface has the lowest pressure. As the Reynolds number and angle of attack are increased, the pressure difference between the upper and lower surfaces is increased. The highest pressure is at the leading edge. Upper surface of NACA 0012 airfoil has the highest velocity vectors. The leading edge has the lowest velocity vectors. For WORTMANN FX 63-137, the slowest velocity is at the leading and trailing edges. The lower surface has lower velocity vectors than the upper surface. 2005 Thesis https://ir.uitm.edu.my/id/eprint/76929/ https://ir.uitm.edu.my/id/eprint/76929/1/76929.pdf text en public degree Universiti Teknologi MARA (UiTM) Faculty of Mechanical Engineering Mohd Ali, Zurriati
institution	Universiti Teknologi MARA
collection	UiTM Institutional Repository
language	English
advisor	Mohd Ali, Zurriati
topic	TL Motor vehicles Aeronautics Astronautics
spellingShingle	TL Motor vehicles Aeronautics Astronautics Yahaya, Zulkifli The computational study on the aerodynamic characteristics of airfoils using fluent / Zulkifli Yahaya
description	Steady-state, two-dimensional CFD calculations were made for the symmetry airfoil, NACA 0012 and cambered airfoil, WORTMANN FX 63-137 using the standard turbulence model, K-B model of commercial code, FLUENT. Comparisons of aerodynamics characteristics, pressure contours, and velocity vectors were made between the two airfoils. The effects of Reynolds numbers, angles of attack, and airfoil profiles on the airfoils were investigated. Results showed that for each and increased Reynolds number with corresponding angle of attack, the cambered airfoil has increasing and higher values of CL and Co than the symmetry airfoil. As the Reynolds number and the angle of attack are increased, the stagnation points of both airfoils are moved further backward to the lower surface. The cambered airfoil, WORTMANN FX 63-137, has clear pressure difference between the upper and the lower surfaces. The lower surfaces have higher pressure than upper surface. The highest pressure is at the leading edge, followed by the pressure at trailing edge. For symmetry airfoil, NACA 0012, 'ihe upper surface has the lowest pressure. As the Reynolds number and angle of attack are increased, the pressure difference between the upper and lower surfaces is increased. The highest pressure is at the leading edge. Upper surface of NACA 0012 airfoil has the highest velocity vectors. The leading edge has the lowest velocity vectors. For WORTMANN FX 63-137, the slowest velocity is at the leading and trailing edges. The lower surface has lower velocity vectors than the upper surface.
format	Thesis
qualification_level	Bachelor degree
author	Yahaya, Zulkifli
author_facet	Yahaya, Zulkifli
author_sort	Yahaya, Zulkifli
title	The computational study on the aerodynamic characteristics of airfoils using fluent / Zulkifli Yahaya
title_short	The computational study on the aerodynamic characteristics of airfoils using fluent / Zulkifli Yahaya
title_full	The computational study on the aerodynamic characteristics of airfoils using fluent / Zulkifli Yahaya
title_fullStr	The computational study on the aerodynamic characteristics of airfoils using fluent / Zulkifli Yahaya
title_full_unstemmed	The computational study on the aerodynamic characteristics of airfoils using fluent / Zulkifli Yahaya
title_sort	computational study on the aerodynamic characteristics of airfoils using fluent / zulkifli yahaya
granting_institution	Universiti Teknologi MARA (UiTM)
granting_department	Faculty of Mechanical Engineering
publishDate	2005
url	https://ir.uitm.edu.my/id/eprint/76929/1/76929.pdf
_version_	1783736130703720448

The computational study on the aerodynamic characteristics of airfoils using fluent / Zulkifli Yahaya

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