Effect of sweep angle and a half sine wave on roll damping derivative of a Delta Wing

This paper presents the effect of sweep angle on a roll of damping derivative of a delta wing with half-sine wave for an attached shock case in supersonic/hypersonic flow has been studied analytically. The Ghosh Strip theory is replicated. By combining this with the similitude at high-speed flows l...

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Main Authors:	Monis, Renita Sharon, Shabana, Aysha, Crasta, Asha, Khan, Sher Afghan
Format:	Article
Language:	English English
Published:	Blue Eyes Intelligence Engineering & Sciences 2019
Subjects:	QA300 Analysis
Online Access:	http://irep.iium.edu.my/73973/ http://irep.iium.edu.my/73973/ http://irep.iium.edu.my/73973/ http://irep.iium.edu.my/73973/1/Asha.pdf http://irep.iium.edu.my/73973/7/73973_Effect%20of%20sweep%20angle%20and%20a%20half%20sine%20wave%20on%20roll%20damping%20derivative%20of%20a%20delta%20wing_Scopus.pdf

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spelling	iium-739732019-11-24T15:41:30Z http://irep.iium.edu.my/73973/ Effect of sweep angle and a half sine wave on roll damping derivative of a Delta Wing Monis, Renita Sharon Shabana, Aysha Crasta, Asha Khan, Sher Afghan QA300 Analysis This paper presents the effect of sweep angle on a roll of damping derivative of a delta wing with half-sine wave for an attached shock case in supersonic/hypersonic flow has been studied analytically. The Ghosh Strip theory is replicated. By combining this with the similitude at high-speed flows lead to giving a piston theory. The initial conditions for the applicability of the theory are that the attached wave must be attached with the leading edge of the wing. The results of the present study reveal that with the increments in the sweep angles; it results in continuous decrease in the roll damping derivative, it is also seen that the magnitude of the decrement for lower sweep angle is considerable as compared to the higher values of the sweep angles due to the drastic change in the surface area of the wing. Roll damping derivative progressively increases with the angle of attack; however, with the increase in the inertia level of the flow, it results in the decrement in the damping derivative and later conforms to the Mach number independence principle. Effect of the leading edge bluntness and viscous effects are neglected. Results have been obtained for the supersonic/hypersonic flow of perfect gases over a wide range of angle of attack, planform area for different Mach numbers. In the present study, attention is on the effect of sweep angle of the wing on roll damping derivative at a different angle of attack and inertia level has been studied. In contemporary theory, Leeward surface is taken along with shock waves attached with the leading edge. Blue Eyes Intelligence Engineering & Sciences 2019-07 Article PeerReviewed application/pdf en http://irep.iium.edu.my/73973/1/Asha.pdf application/pdf en http://irep.iium.edu.my/73973/7/73973_Effect%20of%20sweep%20angle%20and%20a%20half%20sine%20wave%20on%20roll%20damping%20derivative%20of%20a%20delta%20wing_Scopus.pdf Monis, Renita Sharon and Shabana, Aysha and Crasta, Asha and Khan, Sher Afghan (2019) Effect of sweep angle and a half sine wave on roll damping derivative of a Delta Wing. International Journal of Recent Technology and Engineering, 8 (2S3). pp. 984-989. E-ISSN 2277-3878 https://www.ijrte.org/wp-content/uploads/papers/v8i2S3/B11840782S319.pdf 10.35940/ijrte.B1184.0782S319
repository_type	Digital Repository
institution_category	Local University
institution	International Islamic University Malaysia
building	IIUM Repository
collection	Online Access
language	English English
topic	QA300 Analysis
spellingShingle	QA300 Analysis Monis, Renita Sharon Shabana, Aysha Crasta, Asha Khan, Sher Afghan Effect of sweep angle and a half sine wave on roll damping derivative of a Delta Wing
description	This paper presents the effect of sweep angle on a roll of damping derivative of a delta wing with half-sine wave for an attached shock case in supersonic/hypersonic flow has been studied analytically. The Ghosh Strip theory is replicated. By combining this with the similitude at high-speed flows lead to giving a piston theory. The initial conditions for the applicability of the theory are that the attached wave must be attached with the leading edge of the wing. The results of the present study reveal that with the increments in the sweep angles; it results in continuous decrease in the roll damping derivative, it is also seen that the magnitude of the decrement for lower sweep angle is considerable as compared to the higher values of the sweep angles due to the drastic change in the surface area of the wing. Roll damping derivative progressively increases with the angle of attack; however, with the increase in the inertia level of the flow, it results in the decrement in the damping derivative and later conforms to the Mach number independence principle. Effect of the leading edge bluntness and viscous effects are neglected. Results have been obtained for the supersonic/hypersonic flow of perfect gases over a wide range of angle of attack, planform area for different Mach numbers. In the present study, attention is on the effect of sweep angle of the wing on roll damping derivative at a different angle of attack and inertia level has been studied. In contemporary theory, Leeward surface is taken along with shock waves attached with the leading edge.
format	Article
author	Monis, Renita Sharon Shabana, Aysha Crasta, Asha Khan, Sher Afghan
author_facet	Monis, Renita Sharon Shabana, Aysha Crasta, Asha Khan, Sher Afghan
author_sort	Monis, Renita Sharon
title	Effect of sweep angle and a half sine wave on roll damping derivative of a Delta Wing
title_short	Effect of sweep angle and a half sine wave on roll damping derivative of a Delta Wing
title_full	Effect of sweep angle and a half sine wave on roll damping derivative of a Delta Wing
title_fullStr	Effect of sweep angle and a half sine wave on roll damping derivative of a Delta Wing
title_full_unstemmed	Effect of sweep angle and a half sine wave on roll damping derivative of a Delta Wing
title_sort	effect of sweep angle and a half sine wave on roll damping derivative of a delta wing
publisher	Blue Eyes Intelligence Engineering & Sciences
publishDate	2019
url	http://irep.iium.edu.my/73973/ http://irep.iium.edu.my/73973/ http://irep.iium.edu.my/73973/ http://irep.iium.edu.my/73973/1/Asha.pdf http://irep.iium.edu.my/73973/7/73973_Effect%20of%20sweep%20angle%20and%20a%20half%20sine%20wave%20on%20roll%20damping%20derivative%20of%20a%20delta%20wing_Scopus.pdf
first_indexed	2023-09-18T21:44:52Z
last_indexed	2023-09-18T21:44:52Z
_version_	1777413381970460672

Effect of sweep angle and a half sine wave on roll damping derivative of a Delta Wing

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