Estimation of stability derivatives of an oscillating hypersonic delta wings with curved leading edges

Estimation of stability derivatives of an oscillating hypersonic delta wings with curved leading edges

In the present study hypersonic similitude has been used to obtain stability derivatives in pitch and roll of a delta wing with curved leading edges for the attached shock case. A strip theory is used in which strips at different span-wise locations are independent. This combines with the similitude...

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Main Authors: Crasta, Asha, Khan, Sher Afghan
Format: Article
Language:English
Published: International Association of Engineering and Management Education (IAEME) 2012
Subjects:
TL Motor vehicles. Aeronautics. Astronautics
TL780 Rockets
Online Access:http://irep.iium.edu.my/49929/
http://irep.iium.edu.my/49929/
http://irep.iium.edu.my/49929/1/ESTIMATION_OF_STABILITY_DERIVATIVES_OF_AN_OSCILLATING_HYPERSONIC_DELTA_WINGS_WITH_CURVED-paper10.pdf
id iium-49929
recordtype eprints
spelling iium-499292016-04-20T02:17:34Z http://irep.iium.edu.my/49929/ Estimation of stability derivatives of an oscillating hypersonic delta wings with curved leading edges Crasta, Asha Khan, Sher Afghan TL Motor vehicles. Aeronautics. Astronautics TL780 Rockets In the present study hypersonic similitude has been used to obtain stability derivatives in pitch and roll of a delta wing with curved leading edges for the attached shock case. A strip theory is used in which strips at different span-wise locations are independent. This combines with the similitude to give a piston theory. The present theory is valid only for attached shock case. Effects of wave reflection and viscosity have not been taken into account. Some of the results have been compared with those of Hui et al, Ghosh and Liu & Hui. Results have been obtained for hypersonic flow of perfect gas over a wide range of mach numbers, incidences and sweep angles. International Association of Engineering and Management Education (IAEME) 2012-09 Article PeerReviewed application/pdf en http://irep.iium.edu.my/49929/1/ESTIMATION_OF_STABILITY_DERIVATIVES_OF_AN_OSCILLATING_HYPERSONIC_DELTA_WINGS_WITH_CURVED-paper10.pdf Crasta, Asha and Khan, Sher Afghan (2012) Estimation of stability derivatives of an oscillating hypersonic delta wings with curved leading edges. International Journal of Mechanical Engineering & Technology, 3 (3). pp. 483-492. ISSN 0976-6359 http://www.iaeme.com/ijmet.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
Estimation of stability derivatives of an oscillating hypersonic delta wings with curved leading edges
description In the present study hypersonic similitude has been used to obtain stability derivatives in pitch and roll of a delta wing with curved leading edges for the attached shock case. A strip theory is used in which strips at different span-wise locations are independent. This combines with the similitude to give a piston theory. The present theory is valid only for attached shock case. Effects of wave reflection and viscosity have not been taken into account. Some of the results have been compared with those of Hui et al, Ghosh and Liu & Hui. Results have been obtained for hypersonic flow of perfect gas over a wide range of mach numbers, incidences and sweep angles.
format Article
author Crasta, Asha
Khan, Sher Afghan
author_facet Crasta, Asha
Khan, Sher Afghan
author_sort Crasta, Asha
title Estimation of stability derivatives of an oscillating hypersonic delta wings with curved leading edges
title_short Estimation of stability derivatives of an oscillating hypersonic delta wings with curved leading edges
title_full Estimation of stability derivatives of an oscillating hypersonic delta wings with curved leading edges
title_fullStr Estimation of stability derivatives of an oscillating hypersonic delta wings with curved leading edges
title_full_unstemmed Estimation of stability derivatives of an oscillating hypersonic delta wings with curved leading edges
title_sort estimation of stability derivatives of an oscillating hypersonic delta wings with curved leading edges
publisher International Association of Engineering and Management Education (IAEME)
publishDate 2012
url http://irep.iium.edu.my/49929/
http://irep.iium.edu.my/49929/
http://irep.iium.edu.my/49929/1/ESTIMATION_OF_STABILITY_DERIVATIVES_OF_AN_OSCILLATING_HYPERSONIC_DELTA_WINGS_WITH_CURVED-paper10.pdf
first_indexed 2023-09-18T21:10:33Z
last_indexed 2023-09-18T21:10:33Z
_version_ 1777411223258660864

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