Computational and analytical investigation of aerodynamic derivatives of similitude delta wing model at hypersonic speeds

This research paper presents a computational and analytical investigation of aerodynamic derivatives in an oscillating wedge. Unsteady hypersonic similitude has been apprehended for an oscillating wedge with an attached bow shock at a large incidence angle. The problems of instability and shock wave...

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Main Authors:	Bashir, Musavir, Khan, Sher Afghan, Azam, Qummare, Janvekar, Ayub
Format:	Article
Language:	English English
Published:	Faculty of Engineering, Universitas Indonesia 2017
Subjects:	U Military Science (General)
Online Access:	http://irep.iium.edu.my/56874/ http://irep.iium.edu.my/56874/ http://irep.iium.edu.my/56874/ http://irep.iium.edu.my/56874/13/56874_COMPUTATIONAL%20AND%20ANALYTICAL%20INVESTIGATION_article.pdf http://irep.iium.edu.my/56874/7/56874_Computational%20and%20analytical%20investigation_SCOPUS.pdf

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spelling	iium-568742018-04-17T03:04:24Z http://irep.iium.edu.my/56874/ Computational and analytical investigation of aerodynamic derivatives of similitude delta wing model at hypersonic speeds Bashir, Musavir Khan, Sher Afghan Azam, Qummare Janvekar, Ayub U Military Science (General) This research paper presents a computational and analytical investigation of aerodynamic derivatives in an oscillating wedge. Unsteady hypersonic similitude has been apprehended for an oscillating wedge with an attached bow shock at a large incidence angle. The problems of instability and shock waves are generally associated with hypersonic flow and, therefore, it is imperative to evaluate aerodynamic models that can solve these problems. Lighthill’s piston theory is an unsteady aerodynamic model that is valid for an oscillating wedge with an attached shock wave. The analytical solution verifies that both the stiffness and the damping derivatives attain high values when the semi-vertex angle of the wedge is increased, while both derivatives assume lower values at increasing Mach numbers. Similarly, the pressure distribution over the wedge is evaluated to determine the details of how the developing flow cause the instabilities. Our study presents the contour plots of pressure, temperature, density, and Mach number that unravels the positions of flow separations in an oscillating wedge model. Faculty of Engineering, Universitas Indonesia 2017 Article PeerReviewed application/pdf en http://irep.iium.edu.my/56874/13/56874_COMPUTATIONAL%20AND%20ANALYTICAL%20INVESTIGATION_article.pdf application/pdf en http://irep.iium.edu.my/56874/7/56874_Computational%20and%20analytical%20investigation_SCOPUS.pdf Bashir, Musavir and Khan, Sher Afghan and Azam, Qummare and Janvekar, Ayub (2017) Computational and analytical investigation of aerodynamic derivatives of similitude delta wing model at hypersonic speeds. International Journal of Technology, 8 (3). pp. 366-375. ISSN 2086-9614 http://ijtech.eng.ui.ac.id/article/view/176 10.14716/ijtech.v8i3.6319
repository_type	Digital Repository
institution_category	Local University
institution	International Islamic University Malaysia
building	IIUM Repository
collection	Online Access
language	English English
topic	U Military Science (General)
spellingShingle	U Military Science (General) Bashir, Musavir Khan, Sher Afghan Azam, Qummare Janvekar, Ayub Computational and analytical investigation of aerodynamic derivatives of similitude delta wing model at hypersonic speeds
description	This research paper presents a computational and analytical investigation of aerodynamic derivatives in an oscillating wedge. Unsteady hypersonic similitude has been apprehended for an oscillating wedge with an attached bow shock at a large incidence angle. The problems of instability and shock waves are generally associated with hypersonic flow and, therefore, it is imperative to evaluate aerodynamic models that can solve these problems. Lighthill’s piston theory is an unsteady aerodynamic model that is valid for an oscillating wedge with an attached shock wave. The analytical solution verifies that both the stiffness and the damping derivatives attain high values when the semi-vertex angle of the wedge is increased, while both derivatives assume lower values at increasing Mach numbers. Similarly, the pressure distribution over the wedge is evaluated to determine the details of how the developing flow cause the instabilities. Our study presents the contour plots of pressure, temperature, density, and Mach number that unravels the positions of flow separations in an oscillating wedge model.
format	Article
author	Bashir, Musavir Khan, Sher Afghan Azam, Qummare Janvekar, Ayub
author_facet	Bashir, Musavir Khan, Sher Afghan Azam, Qummare Janvekar, Ayub
author_sort	Bashir, Musavir
title	Computational and analytical investigation of aerodynamic derivatives of similitude delta wing model at hypersonic speeds
title_short	Computational and analytical investigation of aerodynamic derivatives of similitude delta wing model at hypersonic speeds
title_full	Computational and analytical investigation of aerodynamic derivatives of similitude delta wing model at hypersonic speeds
title_fullStr	Computational and analytical investigation of aerodynamic derivatives of similitude delta wing model at hypersonic speeds
title_full_unstemmed	Computational and analytical investigation of aerodynamic derivatives of similitude delta wing model at hypersonic speeds
title_sort	computational and analytical investigation of aerodynamic derivatives of similitude delta wing model at hypersonic speeds
publisher	Faculty of Engineering, Universitas Indonesia
publishDate	2017
url	http://irep.iium.edu.my/56874/ http://irep.iium.edu.my/56874/ http://irep.iium.edu.my/56874/ http://irep.iium.edu.my/56874/13/56874_COMPUTATIONAL%20AND%20ANALYTICAL%20INVESTIGATION_article.pdf http://irep.iium.edu.my/56874/7/56874_Computational%20and%20analytical%20investigation_SCOPUS.pdf
first_indexed	2023-09-18T21:20:18Z
last_indexed	2023-09-18T21:20:18Z
_version_	1777411836908404736

Computational and analytical investigation of aerodynamic derivatives of similitude delta wing model at hypersonic speeds

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