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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/56874/13/56874_COMPUTATIONAL%20AND%20ANALYTICAL%20INVESTIGATION_article.pdf
http://irep.iium.edu.my/56874/7/56874_Computational%20and%20analytical%20investigation_SCOPUS.pdf
http://irep.iium.edu.my/56874/
http://ijtech.eng.ui.ac.id/article/view/176
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spelling my.iium.irep.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 REM 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
institution Universiti Islam Antarabangsa Malaysia
building IIUM Library
collection Institutional Repository
continent Asia
country Malaysia
content_provider International Islamic University Malaysia
content_source IIUM Repository (IREP)
url_provider http://irep.iium.edu.my/
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/56874/13/56874_COMPUTATIONAL%20AND%20ANALYTICAL%20INVESTIGATION_article.pdf
http://irep.iium.edu.my/56874/7/56874_Computational%20and%20analytical%20investigation_SCOPUS.pdf
http://irep.iium.edu.my/56874/
http://ijtech.eng.ui.ac.id/article/view/176
_version_ 1643615016922906624
score 13.211869

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