Effect of aspect ratio with angle of attack of an oscillating hypersonic delta wing with straight leading edges

The present study focuses attention on the effect of Aspect ratio of the wing on roll damping moment derivative at various angles of attack and Mach number has been studied. It is found that rolling moment derivative increases with aspect ratio as well as with the angle of attack as the rolling mome...

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Main Authors:	Crasta, Asha, Khan, Sher Afghan
Format:	Article
Language:	English
Published:	IMRF Journals 2015
Subjects:	QA Mathematics TL500 Aeronautics TL780 Rockets
Online Access:	http://irep.iium.edu.my/46635/ http://irep.iium.edu.my/46635/ http://irep.iium.edu.my/46635/1/46635.pdf

id	iium-46635
recordtype	eprints
spelling	iium-466352017-11-16T10:00:19Z http://irep.iium.edu.my/46635/ Effect of aspect ratio with angle of attack of an oscillating hypersonic delta wing with straight leading edges Crasta, Asha Khan, Sher Afghan QA Mathematics TL500 Aeronautics TL780 Rockets The present study focuses attention on the effect of Aspect ratio of the wing on roll damping moment derivative at various angles of attack and Mach number has been studied. It is found that rolling moment derivative increases with aspect ratio as well as with the angle of attack as the rolling moment derivative is linear function of aspect ratio as well as the angle of attack. It is also seen that with the increase in the aspect ratio, roll damping derivatives decreases with increase in Mach number initially and then confirms the Mach number independence principle for large Mach numbers in the hyper-sonic flow regime. The Present theory is valid only when the shock wave is attached with the wing leading edge, for detached shock case the present theory is no more valid and also the flow will be sub-sonic locally leading to flow separation and finally tremendous deceleration in the flow. Also, the effects of wave reflection and viscosity have not been considered in the present study. Results have been obtained for hyper-sonic flow of perfect gases over a wide range of angle of attack, the Mach number, and the aspect ratio. IMRF Journals 2015 Article PeerReviewed application/pdf en http://irep.iium.edu.my/46635/1/46635.pdf Crasta, Asha and Khan, Sher Afghan (2015) Effect of aspect ratio with angle of attack of an oscillating hypersonic delta wing with straight leading edges. Mathematical Sciences International Research Journal, 4 (2). pp. 28-33. ISSN 2278-8697 http://imrf.in/journals.html
repository_type	Digital Repository
institution_category	Local University
institution	International Islamic University Malaysia
building	IIUM Repository
collection	Online Access
language	English
topic	QA Mathematics TL500 Aeronautics TL780 Rockets
spellingShingle	QA Mathematics TL500 Aeronautics TL780 Rockets Crasta, Asha Khan, Sher Afghan Effect of aspect ratio with angle of attack of an oscillating hypersonic delta wing with straight leading edges
description	The present study focuses attention on the effect of Aspect ratio of the wing on roll damping moment derivative at various angles of attack and Mach number has been studied. It is found that rolling moment derivative increases with aspect ratio as well as with the angle of attack as the rolling moment derivative is linear function of aspect ratio as well as the angle of attack. It is also seen that with the increase in the aspect ratio, roll damping derivatives decreases with increase in Mach number initially and then confirms the Mach number independence principle for large Mach numbers in the hyper-sonic flow regime. The Present theory is valid only when the shock wave is attached with the wing leading edge, for detached shock case the present theory is no more valid and also the flow will be sub-sonic locally leading to flow separation and finally tremendous deceleration in the flow. Also, the effects of wave reflection and viscosity have not been considered in the present study. Results have been obtained for hyper-sonic flow of perfect gases over a wide range of angle of attack, the Mach number, and the aspect ratio.
format	Article
author	Crasta, Asha Khan, Sher Afghan
author_facet	Crasta, Asha Khan, Sher Afghan
author_sort	Crasta, Asha
title	Effect of aspect ratio with angle of attack of an oscillating hypersonic delta wing with straight leading edges
title_short	Effect of aspect ratio with angle of attack of an oscillating hypersonic delta wing with straight leading edges
title_full	Effect of aspect ratio with angle of attack of an oscillating hypersonic delta wing with straight leading edges
title_fullStr	Effect of aspect ratio with angle of attack of an oscillating hypersonic delta wing with straight leading edges
title_full_unstemmed	Effect of aspect ratio with angle of attack of an oscillating hypersonic delta wing with straight leading edges
title_sort	effect of aspect ratio with angle of attack of an oscillating hypersonic delta wing with straight leading edges
publisher	IMRF Journals
publishDate	2015
url	http://irep.iium.edu.my/46635/ http://irep.iium.edu.my/46635/ http://irep.iium.edu.my/46635/1/46635.pdf
first_indexed	2023-09-18T21:06:23Z
last_indexed	2023-09-18T21:06:23Z
_version_	1777410961119903744

Effect of aspect ratio with angle of attack of an oscillating hypersonic delta wing with straight leading edges

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