Research onFlows for NACA 2412 airfoil using computational Fluid dynamics method

The comparison between incompressible and compressible flow for aerodynamic coefficients and flow characteristics has been made for NACA 2412 airfoil. The FEM is used to obtain results. The fluid domain of 10C has been constructed to initialize the boundary conditions of incompressible and compressi...

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Main Authors:	Kharulaman, Liyana, Aabid, Abdul, Mehaboobali, Fharukh Ahmed Ghasi, Khan, Sher Afghan
Format:	Article
Language:	English English
Published:	Blue Eyes Intelligence Engineering & Sciences Publication 2019
Subjects:	TL Motor vehicles. Aeronautics. Astronautics
Online Access:	http://irep.iium.edu.my/75891/ http://irep.iium.edu.my/75891/ http://irep.iium.edu.my/75891/ http://irep.iium.edu.my/75891/1/Liyana-paper.pdf http://irep.iium.edu.my/75891/7/75891_Research%20onFlows%20for%20NACA%202412%20%20airfoil%20_scopus.pdf

id	iium-75891
recordtype	eprints
spelling	iium-758912019-12-03T11:08:01Z http://irep.iium.edu.my/75891/ Research onFlows for NACA 2412 airfoil using computational Fluid dynamics method Kharulaman, Liyana Aabid, Abdul Mehaboobali, Fharukh Ahmed Ghasi Khan, Sher Afghan TL Motor vehicles. Aeronautics. Astronautics The comparison between incompressible and compressible flow for aerodynamic coefficients and flow characteristics has been made for NACA 2412 airfoil. The FEM is used to obtain results. The fluid domain of 10C has been constructed to initialize the boundary conditions of incompressible and compressible flow conditions. The structured mesh has been applied in order to achieve accurate results. The Spallart-Allmaras turbulence model has been used to solve both incompressible and compressible flow conditions. The method validation that has been conducted at incompressible flow has shown close agreement between numerical and experimental lift coefficient. From velocity magnitude and static pressure, contours, the compressible flow has the highest-pressure distribution compared to incompressible flow. Therefore, it has been proven that the coefficient of force at ninety degrees to the direction of the flow direction of the airfoil subjected to a variable density flow was much higher compared to incompressible flow. Blue Eyes Intelligence Engineering & Sciences Publication 2019-10 Article PeerReviewed application/pdf en http://irep.iium.edu.my/75891/1/Liyana-paper.pdf application/pdf en http://irep.iium.edu.my/75891/7/75891_Research%20onFlows%20for%20NACA%202412%20%20airfoil%20_scopus.pdf Kharulaman, Liyana and Aabid, Abdul and Mehaboobali, Fharukh Ahmed Ghasi and Khan, Sher Afghan (2019) Research onFlows for NACA 2412 airfoil using computational Fluid dynamics method. International Journal of Engineering and Advanced Technology (IJEAT), 9 (1). pp. 5450-5456. ISSN 2249 – 8958 http://www.ijeat.org 10.35940/ijeat.A3085.109119
repository_type	Digital Repository
institution_category	Local University
institution	International Islamic University Malaysia
building	IIUM Repository
collection	Online Access
language	English English
topic	TL Motor vehicles. Aeronautics. Astronautics
spellingShingle	TL Motor vehicles. Aeronautics. Astronautics Kharulaman, Liyana Aabid, Abdul Mehaboobali, Fharukh Ahmed Ghasi Khan, Sher Afghan Research onFlows for NACA 2412 airfoil using computational Fluid dynamics method
description	The comparison between incompressible and compressible flow for aerodynamic coefficients and flow characteristics has been made for NACA 2412 airfoil. The FEM is used to obtain results. The fluid domain of 10C has been constructed to initialize the boundary conditions of incompressible and compressible flow conditions. The structured mesh has been applied in order to achieve accurate results. The Spallart-Allmaras turbulence model has been used to solve both incompressible and compressible flow conditions. The method validation that has been conducted at incompressible flow has shown close agreement between numerical and experimental lift coefficient. From velocity magnitude and static pressure, contours, the compressible flow has the highest-pressure distribution compared to incompressible flow. Therefore, it has been proven that the coefficient of force at ninety degrees to the direction of the flow direction of the airfoil subjected to a variable density flow was much higher compared to incompressible flow.
format	Article
author	Kharulaman, Liyana Aabid, Abdul Mehaboobali, Fharukh Ahmed Ghasi Khan, Sher Afghan
author_facet	Kharulaman, Liyana Aabid, Abdul Mehaboobali, Fharukh Ahmed Ghasi Khan, Sher Afghan
author_sort	Kharulaman, Liyana
title	Research onFlows for NACA 2412 airfoil using computational Fluid dynamics method
title_short	Research onFlows for NACA 2412 airfoil using computational Fluid dynamics method
title_full	Research onFlows for NACA 2412 airfoil using computational Fluid dynamics method
title_fullStr	Research onFlows for NACA 2412 airfoil using computational Fluid dynamics method
title_full_unstemmed	Research onFlows for NACA 2412 airfoil using computational Fluid dynamics method
title_sort	research onflows for naca 2412 airfoil using computational fluid dynamics method
publisher	Blue Eyes Intelligence Engineering & Sciences Publication
publishDate	2019
url	http://irep.iium.edu.my/75891/ http://irep.iium.edu.my/75891/ http://irep.iium.edu.my/75891/ http://irep.iium.edu.my/75891/1/Liyana-paper.pdf http://irep.iium.edu.my/75891/7/75891_Research%20onFlows%20for%20NACA%202412%20%20airfoil%20_scopus.pdf
first_indexed	2023-09-18T21:47:20Z
last_indexed	2023-09-18T21:47:20Z
_version_	1777413537829748736

Research onFlows for NACA 2412 airfoil using computational Fluid dynamics method

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