Stabilty derivatives in the newtonian limit

This paper presents an analytical method to predict the aerodynamic stability derivatives of oscillating delta wings with curved leading edge. It uses the Ghosh similitude and the strip theory to obtain the expressions for stability derivatives in pitch and roll in the Newtonian limit. The present...

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Main Authors:	Crasta, Asha, Khan, Sher Afghan
Format:	Article
Language:	English
Published:	International Association of Engineering and Management Education (IAEME) 2013
Subjects:	TL Motor vehicles. Aeronautics. Astronautics TL780 Rockets
Online Access:	http://irep.iium.edu.my/49932/ http://irep.iium.edu.my/49932/ http://irep.iium.edu.my/49932/1/published_newtonian_limit_paper-paper12.pdf

id	iium-49932
recordtype	eprints
spelling	iium-499322016-07-18T00:26:01Z http://irep.iium.edu.my/49932/ Stabilty derivatives in the newtonian limit Crasta, Asha Khan, Sher Afghan TL Motor vehicles. Aeronautics. Astronautics TL780 Rockets This paper presents an analytical method to predict the aerodynamic stability derivatives of oscillating delta wings with curved leading edge. It uses the Ghosh similitude and the strip theory to obtain the expressions for stability derivatives in pitch and roll in the Newtonian limit. The present theory gives a quick and approximate method to estimate the stability derivatives which is very handy at the design stage. They are applicable for wings of arbitrary plan form shape at high angles of attack provided the shock wave is attached to the leading edge of the wing. The expressions derived for stability derivatives become exact in the Newtonian limit. The stiffness derivative and damping derivative in pitch and roll are dependent on the geometric parameter of the wing. It is found that stiffness derivative linearly varies with the amplitude. Whenever, the plan form area is increased the stiffness derivative is also increased and vice versa. There is a shift of the center of pressure towards the trailing edge whenever wing plan form is changed from concave to convex plan form. In the case of damping derivative since expressions for these derivatives are non-linear and the same is reflected in all the results. Good agreement is found with existing theories in some special cases. International Association of Engineering and Management Education (IAEME) 2013-12 Article PeerReviewed application/pdf en http://irep.iium.edu.my/49932/1/published_newtonian_limit_paper-paper12.pdf Crasta, Asha and Khan, Sher Afghan (2013) Stabilty derivatives in the newtonian limit. International Journal of Advanced Research in Engineering & Technology (IJARET), 4 (7). pp. 276-289. ISSN 0976-6480 http://iaeme.com/IJARET/index.asp
repository_type	Digital Repository
institution_category	Local University
institution	International Islamic University Malaysia
building	IIUM Repository
collection	Online Access
language	English
topic	TL Motor vehicles. Aeronautics. Astronautics TL780 Rockets
spellingShingle	TL Motor vehicles. Aeronautics. Astronautics TL780 Rockets Crasta, Asha Khan, Sher Afghan Stabilty derivatives in the newtonian limit
description	This paper presents an analytical method to predict the aerodynamic stability derivatives of oscillating delta wings with curved leading edge. It uses the Ghosh similitude and the strip theory to obtain the expressions for stability derivatives in pitch and roll in the Newtonian limit. The present theory gives a quick and approximate method to estimate the stability derivatives which is very handy at the design stage. They are applicable for wings of arbitrary plan form shape at high angles of attack provided the shock wave is attached to the leading edge of the wing. The expressions derived for stability derivatives become exact in the Newtonian limit. The stiffness derivative and damping derivative in pitch and roll are dependent on the geometric parameter of the wing. It is found that stiffness derivative linearly varies with the amplitude. Whenever, the plan form area is increased the stiffness derivative is also increased and vice versa. There is a shift of the center of pressure towards the trailing edge whenever wing plan form is changed from concave to convex plan form. In the case of damping derivative since expressions for these derivatives are non-linear and the same is reflected in all the results. Good agreement is found with existing theories in some special cases.
format	Article
author	Crasta, Asha Khan, Sher Afghan
author_facet	Crasta, Asha Khan, Sher Afghan
author_sort	Crasta, Asha
title	Stabilty derivatives in the newtonian limit
title_short	Stabilty derivatives in the newtonian limit
title_full	Stabilty derivatives in the newtonian limit
title_fullStr	Stabilty derivatives in the newtonian limit
title_full_unstemmed	Stabilty derivatives in the newtonian limit
title_sort	stabilty derivatives in the newtonian limit
publisher	International Association of Engineering and Management Education (IAEME)
publishDate	2013
url	http://irep.iium.edu.my/49932/ http://irep.iium.edu.my/49932/ http://irep.iium.edu.my/49932/1/published_newtonian_limit_paper-paper12.pdf
first_indexed	2023-09-18T21:10:33Z
last_indexed	2023-09-18T21:10:33Z
_version_	1777411223703257088

Stabilty derivatives in the newtonian limit

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