Computation of airfoil boundary layer

Computation of Airfoil boundary layer is an analysis of flow around an airfoil using a CFD commercial packages, GAMBIT/FLUENT. The simulation process will be done to revise the basic theory of complex fluid flow phenomena laminar and turbulent flow around airfoil. The simulation was done for these f...

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Main Author:	Nurfhaizatul Aqma, Chik Aik
Format:	Undergraduates Project Papers
Language:	English
Published:	2007
Subjects:	TA Engineering (General). Civil engineering (General)
Online Access:	http://umpir.ump.edu.my/id/eprint/2333/ http://umpir.ump.edu.my/id/eprint/2333/ http://umpir.ump.edu.my/id/eprint/2333/1/MUHAMMAD_FIKRI_BIN_CHE_MANSHOR__u.PDF

id	ump-2333
recordtype	eprints
spelling	ump-23332015-03-03T07:55:59Z http://umpir.ump.edu.my/id/eprint/2333/ Computation of airfoil boundary layer Nurfhaizatul Aqma, Chik Aik TA Engineering (General). Civil engineering (General) Computation of Airfoil boundary layer is an analysis of flow around an airfoil using a CFD commercial packages, GAMBIT/FLUENT. The simulation process will be done to revise the basic theory of complex fluid flow phenomena laminar and turbulent flow around airfoil. The simulation was done for these flows ensuring in the process that the computations are numerically reliable. Experimental result by Nakayama will be compared with the simulation result for turbulent flow. The flow is 2-dimensional and the grid is all 'C' types meshes. It can be computed as both at low-Reynolds number laminar case and high-Reynolds number turbulent case. The domain is chosen so that the boundaries are far away from the airfoil itself. This choice allows for the use of pressure far-field boundary condition. A number of predefined grids are used to investigate the effect of different grid densities and discretization schemes. The flow is set to come at different angles of coincidence and the velocity magnitude. The discretization schemes used is 1st Order UPWIND scheme and QUICK scheme. It shows that by using QUICK schemes the convergence is far quicker than the 1St Order UPWIND schemes. The drag and lift coefficient obtain for all cases is to be noted. There are two models being tested for turbulent flow, the SpalartAllmaras and k- F, Model. The Spalart-Allmaras Model shows a good prediction of the velocity profiles compared to the k- F Model. 2007-11 Undergraduates Project Papers NonPeerReviewed application/pdf en http://umpir.ump.edu.my/id/eprint/2333/1/MUHAMMAD_FIKRI_BIN_CHE_MANSHOR__u.PDF Nurfhaizatul Aqma, Chik Aik (2007) Computation of airfoil boundary layer. Faculty of Mechanical Engineering, Universiti Malaysia Pahang. http://iportal.ump.edu.my/lib/item?id=chamo:31031&theme=UMP2
repository_type	Digital Repository
institution_category	Local University
institution	Universiti Malaysia Pahang
building	UMP Institutional Repository
collection	Online Access
language	English
topic	TA Engineering (General). Civil engineering (General)
spellingShingle	TA Engineering (General). Civil engineering (General) Nurfhaizatul Aqma, Chik Aik Computation of airfoil boundary layer
description	Computation of Airfoil boundary layer is an analysis of flow around an airfoil using a CFD commercial packages, GAMBIT/FLUENT. The simulation process will be done to revise the basic theory of complex fluid flow phenomena laminar and turbulent flow around airfoil. The simulation was done for these flows ensuring in the process that the computations are numerically reliable. Experimental result by Nakayama will be compared with the simulation result for turbulent flow. The flow is 2-dimensional and the grid is all 'C' types meshes. It can be computed as both at low-Reynolds number laminar case and high-Reynolds number turbulent case. The domain is chosen so that the boundaries are far away from the airfoil itself. This choice allows for the use of pressure far-field boundary condition. A number of predefined grids are used to investigate the effect of different grid densities and discretization schemes. The flow is set to come at different angles of coincidence and the velocity magnitude. The discretization schemes used is 1st Order UPWIND scheme and QUICK scheme. It shows that by using QUICK schemes the convergence is far quicker than the 1St Order UPWIND schemes. The drag and lift coefficient obtain for all cases is to be noted. There are two models being tested for turbulent flow, the SpalartAllmaras and k- F, Model. The Spalart-Allmaras Model shows a good prediction of the velocity profiles compared to the k- F Model.
format	Undergraduates Project Papers
author	Nurfhaizatul Aqma, Chik Aik
author_facet	Nurfhaizatul Aqma, Chik Aik
author_sort	Nurfhaizatul Aqma, Chik Aik
title	Computation of airfoil boundary layer
title_short	Computation of airfoil boundary layer
title_full	Computation of airfoil boundary layer
title_fullStr	Computation of airfoil boundary layer
title_full_unstemmed	Computation of airfoil boundary layer
title_sort	computation of airfoil boundary layer
publishDate	2007
url	http://umpir.ump.edu.my/id/eprint/2333/ http://umpir.ump.edu.my/id/eprint/2333/ http://umpir.ump.edu.my/id/eprint/2333/1/MUHAMMAD_FIKRI_BIN_CHE_MANSHOR__u.PDF
first_indexed	2023-09-18T21:56:02Z
last_indexed	2023-09-18T21:56:02Z
_version_	1777414085255626752

Computation of airfoil boundary layer

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