Stability derivatives of a delta wing with straight leading edge in the Newtonian limit

This paper presents an analytical method to predict the aerodynamic stability derivatives of oscillating delta wings with straight 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 prese...

Full description

Bibliographic Details
Main Authors:	Crasta, Asha, Khan, Sher Afghan
Format:	Article
Language:	English
Published:	IJERA 2013
Subjects:	TL Motor vehicles. Aeronautics. Astronautics TL780 Rockets
Online Access:	http://irep.iium.edu.my/49939/ http://irep.iium.edu.my/49939/ http://irep.iium.edu.my/49939/1/G43023238-paper9.pdf

id	iium-49939
recordtype	eprints
spelling	iium-499392016-07-18T02:26:15Z http://irep.iium.edu.my/49939/ Stability derivatives of a delta wing with straight leading edge 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 straight 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 essential 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 pivot position. In the case of damping derivative since expressions for these derivatives are non-linear and the same is reflected in the results. Roll damping derivative also varies linearly with respect to the angle of attack. When the variation of roll damping derivative was considered, it is found it also, varies linearly with angle of attack for given sweep angle, but with increase in sweep angle there is continuous decrease in the magnitude of the roll damping derivative however, the values differ for different values in sweep angle and the same is reflected in the result when it was studied with respect to sweep angle. From the results it is found that one can arrive at the optimum value of the angle of attack sweep angle which will give the best performance. IJERA 2013-11 Article PeerReviewed application/pdf en http://irep.iium.edu.my/49939/1/G43023238-paper9.pdf Crasta, Asha and Khan, Sher Afghan (2013) Stability derivatives of a delta wing with straight leading edge in the Newtonian limit. International Journal of Engineering Research and Application, 4 (2). pp. 1482-1488. ISSN 2248-9622 http://www.ijera.com
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 Stability derivatives of a delta wing with straight leading edge in the Newtonian limit
description	This paper presents an analytical method to predict the aerodynamic stability derivatives of oscillating delta wings with straight 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 essential 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 pivot position. In the case of damping derivative since expressions for these derivatives are non-linear and the same is reflected in the results. Roll damping derivative also varies linearly with respect to the angle of attack. When the variation of roll damping derivative was considered, it is found it also, varies linearly with angle of attack for given sweep angle, but with increase in sweep angle there is continuous decrease in the magnitude of the roll damping derivative however, the values differ for different values in sweep angle and the same is reflected in the result when it was studied with respect to sweep angle. From the results it is found that one can arrive at the optimum value of the angle of attack sweep angle which will give the best performance.
format	Article
author	Crasta, Asha Khan, Sher Afghan
author_facet	Crasta, Asha Khan, Sher Afghan
author_sort	Crasta, Asha
title	Stability derivatives of a delta wing with straight leading edge in the Newtonian limit
title_short	Stability derivatives of a delta wing with straight leading edge in the Newtonian limit
title_full	Stability derivatives of a delta wing with straight leading edge in the Newtonian limit
title_fullStr	Stability derivatives of a delta wing with straight leading edge in the Newtonian limit
title_full_unstemmed	Stability derivatives of a delta wing with straight leading edge in the Newtonian limit
title_sort	stability derivatives of a delta wing with straight leading edge in the newtonian limit
publisher	IJERA
publishDate	2013
url	http://irep.iium.edu.my/49939/ http://irep.iium.edu.my/49939/ http://irep.iium.edu.my/49939/1/G43023238-paper9.pdf
first_indexed	2023-09-18T21:10:34Z
last_indexed	2023-09-18T21:10:34Z
_version_	1777411224727715840

Stability derivatives of a delta wing with straight leading edge in the Newtonian limit

Similar Items