Effect of aspect ratio with roll moment derivative of a delta wing in supersonic flow

In this paper attention is focussed on study of effect of Aspect ratio of the wing on roll moment derivatives at various angle of attack and Mach number for a Supersonic flow. It is been observed that there is a linear increment in rolling moment derivative with aspect ratio as well as with Angle...

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Main Authors:	Crasta, Asha, Khan, Sher Afghan
Format:	Article
Language:	English
Published:	IRA Publications 2016
Subjects:	TL500 Aeronautics
Online Access:	http://irep.iium.edu.my/50991/ http://irep.iium.edu.my/50991/ http://irep.iium.edu.my/50991/3/Asha_Crasta_-IJAER.pdf

id	iium-50991
recordtype	eprints
spelling	iium-509912016-07-27T09:26:59Z http://irep.iium.edu.my/50991/ Effect of aspect ratio with roll moment derivative of a delta wing in supersonic flow Crasta, Asha Khan, Sher Afghan TL500 Aeronautics In this paper attention is focussed on study of effect of Aspect ratio of the wing on roll moment derivatives at various angle of attack and Mach number for a Supersonic flow. It is been observed that there is a linear increment in rolling moment derivative with aspect ratio as well as with Angle of attack. The reason behind this being rolling moment derivative is a linear function of aspect ratio and angle of attack. The requirement for the validity of the present theory is the attachment of the shock at the leading edge of the wing. Whereas, in the case of detached shock wave, this theory is not valid. IRA Publications 2016-07 Article PeerReviewed application/pdf en http://irep.iium.edu.my/50991/3/Asha_Crasta_-IJAER.pdf Crasta, Asha and Khan, Sher Afghan (2016) Effect of aspect ratio with roll moment derivative of a delta wing in supersonic flow. International Journal of Advances in Engineering Research (IJAER), 12 (1). pp. 10-15. ISSN 2454-1796 E-ISSN 2231-5152 http://www.ijaer.com/images/short_pdf/1465412616_Asha_Crasta_2.pdf
repository_type	Digital Repository
institution_category	Local University
institution	International Islamic University Malaysia
building	IIUM Repository
collection	Online Access
language	English
topic	TL500 Aeronautics
spellingShingle	TL500 Aeronautics Crasta, Asha Khan, Sher Afghan Effect of aspect ratio with roll moment derivative of a delta wing in supersonic flow
description	In this paper attention is focussed on study of effect of Aspect ratio of the wing on roll moment derivatives at various angle of attack and Mach number for a Supersonic flow. It is been observed that there is a linear increment in rolling moment derivative with aspect ratio as well as with Angle of attack. The reason behind this being rolling moment derivative is a linear function of aspect ratio and angle of attack. The requirement for the validity of the present theory is the attachment of the shock at the leading edge of the wing. Whereas, in the case of detached shock wave, this theory is not valid.
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 roll moment derivative of a delta wing in supersonic flow
title_short	Effect of aspect ratio with roll moment derivative of a delta wing in supersonic flow
title_full	Effect of aspect ratio with roll moment derivative of a delta wing in supersonic flow
title_fullStr	Effect of aspect ratio with roll moment derivative of a delta wing in supersonic flow
title_full_unstemmed	Effect of aspect ratio with roll moment derivative of a delta wing in supersonic flow
title_sort	effect of aspect ratio with roll moment derivative of a delta wing in supersonic flow
publisher	IRA Publications
publishDate	2016
url	http://irep.iium.edu.my/50991/ http://irep.iium.edu.my/50991/ http://irep.iium.edu.my/50991/3/Asha_Crasta_-IJAER.pdf
first_indexed	2023-09-18T21:12:09Z
last_indexed	2023-09-18T21:12:09Z
_version_	1777411324345581568

Effect of aspect ratio with roll moment derivative of a delta wing in supersonic flow

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