Estimation of damping derivatives for delta wings in hypersonic flow for straight leading edge

Accurate estimation of the aerodynamic stability derivatives of airplanes is essential to evaluate the performance of the aircraft, whether civilian or military. Theoretical prediction methods for the dynamic stability derivatives at high angles of attack have not advanced, and in the present paper...

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Main Authors:	Renita, sharon Monis, Crasta, Asha, Khan, Sher Afghan
Format:	Article
Language:	English English
Published:	Transstellar Journal Publications and Research Consultancy Private Limited (TJPRC) 2019
Subjects:	QA297 Numerical Analysis
Online Access:	http://irep.iium.edu.my/75483/ http://irep.iium.edu.my/75483/ http://irep.iium.edu.my/75483/ http://irep.iium.edu.my/75483/1/2-67-1571463142-IJMPERDOCT201922.pdf http://irep.iium.edu.my/75483/7/75483_Estimation%20of%20damping%20derivatives_scopus.pdf

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recordtype	eprints
spelling	iium-754832020-03-16T10:18:19Z http://irep.iium.edu.my/75483/ Estimation of damping derivatives for delta wings in hypersonic flow for straight leading edge Renita, sharon Monis Crasta, Asha Khan, Sher Afghan QA297 Numerical Analysis Accurate estimation of the aerodynamic stability derivatives of airplanes is essential to evaluate the performance of the aircraft, whether civilian or military. Theoretical prediction methods for the dynamic stability derivatives at high angles of attack have not advanced, and in the present paper, an attempt has been made to study the effect of damping derivatives for delta wings for different angles of incidence, and the Mach number for a wing whose leading edge is straight. In this paper, the flow is considered to be unsteady flow and also considering the effect of the Leeward surface along with the shock waves and the expansion waves. The theory developed in the present paper considering the unsteady effects, the results have been estimated for speed flows for air assuming the air to behave as perfect gas for a range of angle of incidence and the inertia level. The results show that for Mach number M = 7 and above the damping derivatives become independent of inertia level. Increase in the damping derivatives is substantial when the angle δ is increased from 5 to 10 degrees Transstellar Journal Publications and Research Consultancy Private Limited (TJPRC) 2019-10-19 Article PeerReviewed application/pdf en http://irep.iium.edu.my/75483/1/2-67-1571463142-IJMPERDOCT201922.pdf application/pdf en http://irep.iium.edu.my/75483/7/75483_Estimation%20of%20damping%20derivatives_scopus.pdf Renita, sharon Monis and Crasta, Asha and Khan, Sher Afghan (2019) Estimation of damping derivatives for delta wings in hypersonic flow for straight leading edge. International Journal of Mechanical and Production Engineering Research and Development, 9 (5). pp. 255-264. ISSN 2249-6890 E-ISSN 2249-8001 http://www.tjprc.org/ 10.24247/ijmperdoct201922
repository_type	Digital Repository
institution_category	Local University
institution	International Islamic University Malaysia
building	IIUM Repository
collection	Online Access
language	English English
topic	QA297 Numerical Analysis
spellingShingle	QA297 Numerical Analysis Renita, sharon Monis Crasta, Asha Khan, Sher Afghan Estimation of damping derivatives for delta wings in hypersonic flow for straight leading edge
description	Accurate estimation of the aerodynamic stability derivatives of airplanes is essential to evaluate the performance of the aircraft, whether civilian or military. Theoretical prediction methods for the dynamic stability derivatives at high angles of attack have not advanced, and in the present paper, an attempt has been made to study the effect of damping derivatives for delta wings for different angles of incidence, and the Mach number for a wing whose leading edge is straight. In this paper, the flow is considered to be unsteady flow and also considering the effect of the Leeward surface along with the shock waves and the expansion waves. The theory developed in the present paper considering the unsteady effects, the results have been estimated for speed flows for air assuming the air to behave as perfect gas for a range of angle of incidence and the inertia level. The results show that for Mach number M = 7 and above the damping derivatives become independent of inertia level. Increase in the damping derivatives is substantial when the angle δ is increased from 5 to 10 degrees
format	Article
author	Renita, sharon Monis Crasta, Asha Khan, Sher Afghan
author_facet	Renita, sharon Monis Crasta, Asha Khan, Sher Afghan
author_sort	Renita, sharon Monis
title	Estimation of damping derivatives for delta wings in hypersonic flow for straight leading edge
title_short	Estimation of damping derivatives for delta wings in hypersonic flow for straight leading edge
title_full	Estimation of damping derivatives for delta wings in hypersonic flow for straight leading edge
title_fullStr	Estimation of damping derivatives for delta wings in hypersonic flow for straight leading edge
title_full_unstemmed	Estimation of damping derivatives for delta wings in hypersonic flow for straight leading edge
title_sort	estimation of damping derivatives for delta wings in hypersonic flow for straight leading edge
publisher	Transstellar Journal Publications and Research Consultancy Private Limited (TJPRC)
publishDate	2019
url	http://irep.iium.edu.my/75483/ http://irep.iium.edu.my/75483/ http://irep.iium.edu.my/75483/ http://irep.iium.edu.my/75483/1/2-67-1571463142-IJMPERDOCT201922.pdf http://irep.iium.edu.my/75483/7/75483_Estimation%20of%20damping%20derivatives_scopus.pdf
first_indexed	2023-09-18T21:46:48Z
last_indexed	2023-09-18T21:46:48Z
_version_	1777413504418971648

Estimation of damping derivatives for delta wings in hypersonic flow for straight leading edge

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