Effect of angle of attack on stiffness derivative of an oscillating supersonic delta wing with curved leading edges

In the Present paper effect of angle of incidence on Stiffness derivative of a delta wing with Curved leading edges for attached shock case in Supersonic Flow has been studied. A Strip theory is used in which strips at different span wise location are independent of each other. This combines with si...

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Main Authors:	Crasta, Asha, Khan, Sher Afghan
Format:	Article
Language:	English
Published:	International Organozation of Scientific Research (IOSR) Journals 2014
Subjects:	TL787 Astronautics
Online Access:	http://irep.iium.edu.my/49935/ http://irep.iium.edu.my/49935/ http://irep.iium.edu.my/49935/ http://irep.iium.edu.my/49935/1/49935.pdf

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recordtype	eprints
spelling	iium-499352018-06-11T05:03:26Z http://irep.iium.edu.my/49935/ Effect of angle of attack on stiffness derivative of an oscillating supersonic delta wing with curved leading edges Crasta, Asha Khan, Sher Afghan TL787 Astronautics In the Present paper effect of angle of incidence on Stiffness derivative of a delta wing with Curved leading edges for attached shock case in Supersonic Flow has been studied. A Strip theory is used in which strips at different span wise location are independent of each other. This combines with similitude to give a piston theory which gives closed form solutions for stiffness derivatives at low supersonic to high supersonic Mach numbers. From the results it is seen that with the increase in the Mach number, there is a continuous decrease in the magnitude of stiffness derivatives for all the Mach number tested, however, the magnitude of decrement for different inertia level will differ. It is seen that with the increase in the angle of attack the stiffness derivative increases linearly, nevertheless, this linear behavior limit themselves for different Mach numbers. For Mach number M = 2, this limiting value of validity is fifteen degrees, for Mach 2.5 & 3, it is twenty five degrees, whereas, for Mach 3.5 & 4 it becomes thirty five degrees, when these stability derivatives were considered at various pivot positions; namely at h = 0.0, 0.4, 0.6, and 1.0. After scanning the results it was observed that with the shift of the pivot position from the leading edge to the trailing edge, the magnitude of stiffness and the damping derivatives continue to decrease progressively. Results have been obtained for supersonic flow of perfect gases over a wide range of angle of attack and Mach number. The effect of real gas, leading edge bluntness of the wing, shock motion, and secondary wave reflections are neglected. International Organozation of Scientific Research (IOSR) Journals 2014-10 Article PeerReviewed application/pdf en http://irep.iium.edu.my/49935/1/49935.pdf Crasta, Asha and Khan, Sher Afghan (2014) Effect of angle of attack on stiffness derivative of an oscillating supersonic delta wing with curved leading edges. IOSR Journal of Mechanical and Civil Engineering (IOSR-JMCE), 11 (6vIII). pp. 12-25. ISSN 2320-334X E-ISSN 2278-1684 http://www.iosrjournals.org/iosr-jmce/papers/vol11-issue6/Version-3/C011631225.pdf 10.9790/1684-11280411
repository_type	Digital Repository
institution_category	Local University
institution	International Islamic University Malaysia
building	IIUM Repository
collection	Online Access
language	English
topic	TL787 Astronautics
spellingShingle	TL787 Astronautics Crasta, Asha Khan, Sher Afghan Effect of angle of attack on stiffness derivative of an oscillating supersonic delta wing with curved leading edges
description	In the Present paper effect of angle of incidence on Stiffness derivative of a delta wing with Curved leading edges for attached shock case in Supersonic Flow has been studied. A Strip theory is used in which strips at different span wise location are independent of each other. This combines with similitude to give a piston theory which gives closed form solutions for stiffness derivatives at low supersonic to high supersonic Mach numbers. From the results it is seen that with the increase in the Mach number, there is a continuous decrease in the magnitude of stiffness derivatives for all the Mach number tested, however, the magnitude of decrement for different inertia level will differ. It is seen that with the increase in the angle of attack the stiffness derivative increases linearly, nevertheless, this linear behavior limit themselves for different Mach numbers. For Mach number M = 2, this limiting value of validity is fifteen degrees, for Mach 2.5 & 3, it is twenty five degrees, whereas, for Mach 3.5 & 4 it becomes thirty five degrees, when these stability derivatives were considered at various pivot positions; namely at h = 0.0, 0.4, 0.6, and 1.0. After scanning the results it was observed that with the shift of the pivot position from the leading edge to the trailing edge, the magnitude of stiffness and the damping derivatives continue to decrease progressively. Results have been obtained for supersonic flow of perfect gases over a wide range of angle of attack and Mach number. The effect of real gas, leading edge bluntness of the wing, shock motion, and secondary wave reflections are neglected.
format	Article
author	Crasta, Asha Khan, Sher Afghan
author_facet	Crasta, Asha Khan, Sher Afghan
author_sort	Crasta, Asha
title	Effect of angle of attack on stiffness derivative of an oscillating supersonic delta wing with curved leading edges
title_short	Effect of angle of attack on stiffness derivative of an oscillating supersonic delta wing with curved leading edges
title_full	Effect of angle of attack on stiffness derivative of an oscillating supersonic delta wing with curved leading edges
title_fullStr	Effect of angle of attack on stiffness derivative of an oscillating supersonic delta wing with curved leading edges
title_full_unstemmed	Effect of angle of attack on stiffness derivative of an oscillating supersonic delta wing with curved leading edges
title_sort	effect of angle of attack on stiffness derivative of an oscillating supersonic delta wing with curved leading edges
publisher	International Organozation of Scientific Research (IOSR) Journals
publishDate	2014
url	http://irep.iium.edu.my/49935/ http://irep.iium.edu.my/49935/ http://irep.iium.edu.my/49935/ http://irep.iium.edu.my/49935/1/49935.pdf
first_indexed	2023-09-18T21:10:34Z
last_indexed	2023-09-18T21:10:34Z
_version_	1777411224140513280

Effect of angle of attack on stiffness derivative of an oscillating supersonic delta wing with curved leading edges

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