Estimation of aerodynamic derivatives in pitch of a wedge in hypersonic flow

n the present paper a theory for 2D slender bodies at high angle of attack in hypersonic flow has been developed to determine the aerodynamic derivatives in pitch for different Mach numbers. The present theory has been applied to a sharp thick wedge with attached shock case. Using the theory, a rela...

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Main Authors:	Shanbhag, Pavithra, Lavanya, S, Khan, Sher Afghan, Crasta, Asha
Format:	Article
Language:	English
Published:	Indian Society for Education and Environment & Informatics Publishing Limited 2016
Subjects:	QB Astronomy
Online Access:	http://irep.iium.edu.my/53877/ http://irep.iium.edu.my/53877/ http://irep.iium.edu.my/53877/ http://irep.iium.edu.my/53877/1/SAKHAN.pdf

id	iium-53877
recordtype	eprints
spelling	iium-538772017-01-06T00:31:01Z http://irep.iium.edu.my/53877/ Estimation of aerodynamic derivatives in pitch of a wedge in hypersonic flow Shanbhag, Pavithra Lavanya, S Khan, Sher Afghan Crasta, Asha QB Astronomy n the present paper a theory for 2D slender bodies at high angle of attack in hypersonic flow has been developed to determine the aerodynamic derivatives in pitch for different Mach numbers. The present theory has been applied to a sharp thick wedge with attached shock case. Using the theory, a relation for a piston moving in a cylinder at any velocity and relations for stiffness and damping derivatives are obtained for zero incidence of the wedge and it is found to be dependent on flight Mach number and wedge semi vertex angle. The present method includes the thin wedge case as well, which was covered by Lighthill piston theory, and applies only for small amplitude and low reduced frequency case. Effect of viscosity and secondary wave reflections have been neglected. The results are obtained for wedges of different semi vertex angles and Mach numbers. It is observed that the stiffness and Damping derivatives increase with increase in the semi vertex angle and decrease with an increase in Mach number. At very high Mach number the Mach number independence principle holds good. Indian Society for Education and Environment & Informatics Publishing Limited 2016-09 Article PeerReviewed application/pdf en http://irep.iium.edu.my/53877/1/SAKHAN.pdf Shanbhag, Pavithra and Lavanya, S and Khan, Sher Afghan and Crasta, Asha (2016) Estimation of aerodynamic derivatives in pitch of a wedge in hypersonic flow. Indian Journal of Science and Technology, 9 (34). pp. 1-4. ISSN 0974-6846 E-ISSN 0974-5645 file:///C:/Users/user/Downloads/100958-213033-1-PB.pdf 10.17485/v9i34/100958
repository_type	Digital Repository
institution_category	Local University
institution	International Islamic University Malaysia
building	IIUM Repository
collection	Online Access
language	English
topic	QB Astronomy
spellingShingle	QB Astronomy Shanbhag, Pavithra Lavanya, S Khan, Sher Afghan Crasta, Asha Estimation of aerodynamic derivatives in pitch of a wedge in hypersonic flow
description	n the present paper a theory for 2D slender bodies at high angle of attack in hypersonic flow has been developed to determine the aerodynamic derivatives in pitch for different Mach numbers. The present theory has been applied to a sharp thick wedge with attached shock case. Using the theory, a relation for a piston moving in a cylinder at any velocity and relations for stiffness and damping derivatives are obtained for zero incidence of the wedge and it is found to be dependent on flight Mach number and wedge semi vertex angle. The present method includes the thin wedge case as well, which was covered by Lighthill piston theory, and applies only for small amplitude and low reduced frequency case. Effect of viscosity and secondary wave reflections have been neglected. The results are obtained for wedges of different semi vertex angles and Mach numbers. It is observed that the stiffness and Damping derivatives increase with increase in the semi vertex angle and decrease with an increase in Mach number. At very high Mach number the Mach number independence principle holds good.
format	Article
author	Shanbhag, Pavithra Lavanya, S Khan, Sher Afghan Crasta, Asha
author_facet	Shanbhag, Pavithra Lavanya, S Khan, Sher Afghan Crasta, Asha
author_sort	Shanbhag, Pavithra
title	Estimation of aerodynamic derivatives in pitch of a wedge in hypersonic flow
title_short	Estimation of aerodynamic derivatives in pitch of a wedge in hypersonic flow
title_full	Estimation of aerodynamic derivatives in pitch of a wedge in hypersonic flow
title_fullStr	Estimation of aerodynamic derivatives in pitch of a wedge in hypersonic flow
title_full_unstemmed	Estimation of aerodynamic derivatives in pitch of a wedge in hypersonic flow
title_sort	estimation of aerodynamic derivatives in pitch of a wedge in hypersonic flow
publisher	Indian Society for Education and Environment & Informatics Publishing Limited
publishDate	2016
url	http://irep.iium.edu.my/53877/ http://irep.iium.edu.my/53877/ http://irep.iium.edu.my/53877/ http://irep.iium.edu.my/53877/1/SAKHAN.pdf
first_indexed	2023-09-18T21:16:12Z
last_indexed	2023-09-18T21:16:12Z
_version_	1777411579265941504

Estimation of aerodynamic derivatives in pitch of a wedge in hypersonic flow

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