Oscillating supersonic delta wings with curved leading edges

Oscillating supersonic delta wings with curved leading edges

In the present study Supersonic similitude has been used to obtain stability derivatives in pitch and roll of a delta wing 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 theo...

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Main Authors: Khan, Sher Afghan, Crasta , Asha
Format: Article
Language:English
Published: The Jangjeon Mathematical Society (JMS) 2010
Subjects:
QA75 Electronic computers. Computer science
Online Access:http://irep.iium.edu.my/49812/
http://irep.iium.edu.my/49812/
http://irep.iium.edu.my/49812/1/asha-crasta.pdf
id iium-49812
recordtype eprints
spelling iium-498122016-07-18T07:56:52Z http://irep.iium.edu.my/49812/ Oscillating supersonic delta wings with curved leading edges Khan, Sher Afghan Crasta , Asha QA75 Electronic computers. Computer science In the present study Supersonic similitude has been used to obtain stability derivatives in pitch and roll of a delta wing 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 re ection and viscosity have not been taken into account. Some of the results have been compared with those of Hui et al (1982), Ghosh (1984), and Liu and Hui (1977). Results have been obtained for supersonic ow of perfect gas over a wide range of Mach numbers, incidences and sweep angles. A good agreement is obtained with Hui et al in some special cases. The Jangjeon Mathematical Society (JMS) 2010-07 Article PeerReviewed application/pdf en http://irep.iium.edu.my/49812/1/asha-crasta.pdf Khan, Sher Afghan and Crasta , Asha (2010) Oscillating supersonic delta wings with curved leading edges. Advanced Studies in Contemporary Mathematics, 20 (3). pp. 359-372. ISSN 1229-3067 http://www.jangjeon.or.kr/etc/Search.html?division=ASCM&year=2010
repository_type Digital Repository
institution_category Local University
institution International Islamic University Malaysia
building IIUM Repository
collection Online Access
language English
topic QA75 Electronic computers. Computer science
spellingShingle QA75 Electronic computers. Computer science
Khan, Sher Afghan
Crasta , Asha
Oscillating supersonic delta wings with curved leading edges
description In the present study Supersonic similitude has been used to obtain stability derivatives in pitch and roll of a delta wing 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 re ection and viscosity have not been taken into account. Some of the results have been compared with those of Hui et al (1982), Ghosh (1984), and Liu and Hui (1977). Results have been obtained for supersonic ow of perfect gas over a wide range of Mach numbers, incidences and sweep angles. A good agreement is obtained with Hui et al in some special cases.
format Article
author Khan, Sher Afghan
Crasta , Asha
author_facet Khan, Sher Afghan
Crasta , Asha
author_sort Khan, Sher Afghan
title Oscillating supersonic delta wings with curved leading edges
title_short Oscillating supersonic delta wings with curved leading edges
title_full Oscillating supersonic delta wings with curved leading edges
title_fullStr Oscillating supersonic delta wings with curved leading edges
title_full_unstemmed Oscillating supersonic delta wings with curved leading edges
title_sort oscillating supersonic delta wings with curved leading edges
publisher The Jangjeon Mathematical Society (JMS)
publishDate 2010
url http://irep.iium.edu.my/49812/
http://irep.iium.edu.my/49812/
http://irep.iium.edu.my/49812/1/asha-crasta.pdf
first_indexed 2023-09-18T21:10:22Z
last_indexed 2023-09-18T21:10:22Z
_version_ 1777411211910971392

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