Cover Image

Computational Procedure to Investigate the Boundary Layer Growth Parameters on Conventional Aerfoil

This work includes computational procedure to solve Navier-Stocks equation of viscous flow over 4415 airfoil. Three computer programs have been established to predict the boundary layer growth parameters over the selected airfoil at different angles of attack and different Reynolds numbers. The resu...

Full description

Saved in:
Bibliographic Details
Main Authors: Al-Kayiem, Hussain H., Darwish, A.A., Mahmod, Y.A.
Format: Citation Index Journal
Published: University of Technology - Baghdad 1998
Subjects:
TJ Mechanical engineering and machinery
U Military Science (General)
Online Access:http://eprints.utp.edu.my/4123/1/1.pdf
http://eprints.utp.edu.my/4123/
Tags: Add Tag
No Tags, Be the first to tag this record!
id my.utp.eprints.4123
record_format eprints
spelling my.utp.eprints.41232013-02-28T14:34:54Z Computational Procedure to Investigate the Boundary Layer Growth Parameters on Conventional Aerfoil Al-Kayiem, Hussain H. Darwish, A.A. Mahmod, Y.A. TJ Mechanical engineering and machinery U Military Science (General) This work includes computational procedure to solve Navier-Stocks equation of viscous flow over 4415 airfoil. Three computer programs have been established to predict the boundary layer growth parameters over the selected airfoil at different angles of attack and different Reynolds numbers. The results have demonstrated that the procedure is capable to predict the boundary layer parameters and position of the separation point is determined correctly at each tested angle of attack. University of Technology - Baghdad 1998 Citation Index Journal PeerReviewed application/pdf http://eprints.utp.edu.my/4123/1/1.pdf Al-Kayiem, Hussain H. and Darwish, A.A. and Mahmod, Y.A. (1998) Computational Procedure to Investigate the Boundary Layer Growth Parameters on Conventional Aerfoil. [Citation Index Journal] http://eprints.utp.edu.my/4123/
institution Universiti Teknologi Petronas
building UTP Resource Centre
collection Institutional Repository
continent Asia
country Malaysia
content_provider Universiti Teknologi Petronas
content_source UTP Institutional Repository
url_provider http://eprints.utp.edu.my/
topic TJ Mechanical engineering and machinery
U Military Science (General)
spellingShingle TJ Mechanical engineering and machinery
U Military Science (General)
Al-Kayiem, Hussain H.
Darwish, A.A.
Mahmod, Y.A.
Computational Procedure to Investigate the Boundary Layer Growth Parameters on Conventional Aerfoil
description This work includes computational procedure to solve Navier-Stocks equation of viscous flow over 4415 airfoil. Three computer programs have been established to predict the boundary layer growth parameters over the selected airfoil at different angles of attack and different Reynolds numbers. The results have demonstrated that the procedure is capable to predict the boundary layer parameters and position of the separation point is determined correctly at each tested angle of attack.
format Citation Index Journal
author Al-Kayiem, Hussain H.
Darwish, A.A.
Mahmod, Y.A.
author_facet Al-Kayiem, Hussain H.
Darwish, A.A.
Mahmod, Y.A.
author_sort Al-Kayiem, Hussain H.
title Computational Procedure to Investigate the Boundary Layer Growth Parameters on Conventional Aerfoil
title_short Computational Procedure to Investigate the Boundary Layer Growth Parameters on Conventional Aerfoil
title_full Computational Procedure to Investigate the Boundary Layer Growth Parameters on Conventional Aerfoil
title_fullStr Computational Procedure to Investigate the Boundary Layer Growth Parameters on Conventional Aerfoil
title_full_unstemmed Computational Procedure to Investigate the Boundary Layer Growth Parameters on Conventional Aerfoil
title_sort computational procedure to investigate the boundary layer growth parameters on conventional aerfoil
publisher University of Technology - Baghdad
publishDate 1998
url http://eprints.utp.edu.my/4123/1/1.pdf
http://eprints.utp.edu.my/4123/
_version_ 1738655321692307456
score 13.211869

Similar Items