Optimization of two-dimensional wedge flow field at supersonic Mach number

In the present condition, there is a high demand for exact solutions through analytical, computational and measurements in the field of aerospace engineering. For wind tunnel testing it is difficult to bear the cost because of highly expensive materials needed for wind tunnel testing and the time ne...

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Main Authors:	Khan, Sher Afghan, Aabid, Abdul, Mokashi, Imran, Al-Robaian, Abdul Rehman Abdullah, Alsagri, Ali Sulaiman
Format:	Article
Language:	English English
Published:	Penerbit Akademia Baru 2019
Subjects:	QA297 Numerical Analysis
Online Access:	http://irep.iium.edu.my/72295/ http://irep.iium.edu.my/72295/ http://irep.iium.edu.my/72295/1/72295_Optimization%20of%20Two-dimensional.pdf http://irep.iium.edu.my/72295/7/72295_Optimization%20of%20Two-dimensional_scopus.pdf

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recordtype	eprints
spelling	iium-722952019-08-30T09:14:58Z http://irep.iium.edu.my/72295/ Optimization of two-dimensional wedge flow field at supersonic Mach number Khan, Sher Afghan Aabid, Abdul Mokashi, Imran Al-Robaian, Abdul Rehman Abdullah Alsagri, Ali Sulaiman QA297 Numerical Analysis In the present condition, there is a high demand for exact solutions through analytical, computational and measurements in the field of aerospace engineering. For wind tunnel testing it is difficult to bear the cost because of highly expensive materials needed for wind tunnel testing and the time needed to accomplish the experiments. Therefore, in this paper, analytical and numerical methods are used to evaluate the flow field over a wedge at supersonic Mach numbers for attached as well as detached shock cases. The wedge with the various half-wedge angle at Mach number 2 has been considered for the simulation. Closed form solutions are obtained for the various semi-vertex angle of the wedge. Supersonic similarity parameter has been used to obtain the pressure distribution over wedge at a different angle of attack with attached and detached shock wave cases. Results are in good agreement with the theoretical results of the shock-expansion theory. The analytical results are compared with those obtained by simulation. The results are obtained for pressure, temperature, Mach number, and the density using ANSYS code are in good agreement with the results obtained analytically. Penerbit Akademia Baru 2019-05-20 Article PeerReviewed application/pdf en http://irep.iium.edu.my/72295/1/72295_Optimization%20of%20Two-dimensional.pdf application/pdf en http://irep.iium.edu.my/72295/7/72295_Optimization%20of%20Two-dimensional_scopus.pdf Khan, Sher Afghan and Aabid, Abdul and Mokashi, Imran and Al-Robaian, Abdul Rehman Abdullah and Alsagri, Ali Sulaiman (2019) Optimization of two-dimensional wedge flow field at supersonic Mach number. CFD Letters, 11 (5). pp. 80-97. ISSN 2180-1363 http://www.akademiabaru.com/doc/CFDLV11_N5_P80_97.pdf
repository_type	Digital Repository
institution_category	Local University
institution	International Islamic University Malaysia
building	IIUM Repository
collection	Online Access
language	English English
topic	QA297 Numerical Analysis
spellingShingle	QA297 Numerical Analysis Khan, Sher Afghan Aabid, Abdul Mokashi, Imran Al-Robaian, Abdul Rehman Abdullah Alsagri, Ali Sulaiman Optimization of two-dimensional wedge flow field at supersonic Mach number
description	In the present condition, there is a high demand for exact solutions through analytical, computational and measurements in the field of aerospace engineering. For wind tunnel testing it is difficult to bear the cost because of highly expensive materials needed for wind tunnel testing and the time needed to accomplish the experiments. Therefore, in this paper, analytical and numerical methods are used to evaluate the flow field over a wedge at supersonic Mach numbers for attached as well as detached shock cases. The wedge with the various half-wedge angle at Mach number 2 has been considered for the simulation. Closed form solutions are obtained for the various semi-vertex angle of the wedge. Supersonic similarity parameter has been used to obtain the pressure distribution over wedge at a different angle of attack with attached and detached shock wave cases. Results are in good agreement with the theoretical results of the shock-expansion theory. The analytical results are compared with those obtained by simulation. The results are obtained for pressure, temperature, Mach number, and the density using ANSYS code are in good agreement with the results obtained analytically.
format	Article
author	Khan, Sher Afghan Aabid, Abdul Mokashi, Imran Al-Robaian, Abdul Rehman Abdullah Alsagri, Ali Sulaiman
author_facet	Khan, Sher Afghan Aabid, Abdul Mokashi, Imran Al-Robaian, Abdul Rehman Abdullah Alsagri, Ali Sulaiman
author_sort	Khan, Sher Afghan
title	Optimization of two-dimensional wedge flow field at supersonic Mach number
title_short	Optimization of two-dimensional wedge flow field at supersonic Mach number
title_full	Optimization of two-dimensional wedge flow field at supersonic Mach number
title_fullStr	Optimization of two-dimensional wedge flow field at supersonic Mach number
title_full_unstemmed	Optimization of two-dimensional wedge flow field at supersonic Mach number
title_sort	optimization of two-dimensional wedge flow field at supersonic mach number
publisher	Penerbit Akademia Baru
publishDate	2019
url	http://irep.iium.edu.my/72295/ http://irep.iium.edu.my/72295/ http://irep.iium.edu.my/72295/1/72295_Optimization%20of%20Two-dimensional.pdf http://irep.iium.edu.my/72295/7/72295_Optimization%20of%20Two-dimensional_scopus.pdf
first_indexed	2023-09-18T21:42:25Z
last_indexed	2023-09-18T21:42:25Z
_version_	1777413228725272576

Optimization of two-dimensional wedge flow field at supersonic Mach number

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