Oscillating supersonic delta wing with straight leading edges
A Supersonic similitude has been used to obtain stability derivatives in pitch and roll of a delta wing with straight leading edge for the attached shock case. Ghosh’s strip theory is been used in which strips at different span wise locations are independent of each other. This combines with the s...
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| Format: | Article |
| Language: | English |
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IJCER
2012
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| Online Access: | http://irep.iium.edu.my/49942/ http://irep.iium.edu.my/49942/ http://irep.iium.edu.my/49942/1/JO2512261233-print-paper8.pdf |
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eprints |
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iium-499422016-08-11T03:11:13Z http://irep.iium.edu.my/49942/ Oscillating supersonic delta wing with straight leading edges Crasta, Asha Khan, Sher Afghan TL Motor vehicles. Aeronautics. Astronautics A Supersonic similitude has been used to obtain stability derivatives in pitch and roll of a delta wing with straight leading edge for the attached shock case. Ghosh’s strip theory is been used in which strips at different span wise locations are independent of each other. This combines with the similitude to give a piston theory which gives the closed form of solution to stability derivatives in pitch and roll. Some of the results obtained have been compared with those of Hui et al ,Ghosh and Lui &Hui. Results have been obtained for supersonic flow of perfect gas over a wide range of Mach numbers, incidences and sweep angles. IJCER 2012-09 Article PeerReviewed application/pdf en http://irep.iium.edu.my/49942/1/JO2512261233-print-paper8.pdf Crasta, Asha and Khan, Sher Afghan (2012) Oscillating supersonic delta wing with straight leading edges. International Journal of Computational Engineering Research,, 2 (5). pp. 1226-1233. ISSN 2250-3005 http://www.ijceronline.com/papers/Vol2_issue5/JO2512261233.pdf |
| 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 |
| spellingShingle |
TL Motor vehicles. Aeronautics. Astronautics Crasta, Asha Khan, Sher Afghan Oscillating supersonic delta wing with straight leading edges |
| description |
A Supersonic similitude has been used to obtain stability derivatives in pitch and roll of a delta wing with straight leading edge
for the attached shock case. Ghosh’s strip theory is been used in which strips at different span wise locations are independent
of each other. This combines with the similitude to give a piston theory which gives the closed form of solution to stability
derivatives in pitch and roll. Some of the results obtained have been compared with those of Hui et al ,Ghosh and Lui &Hui.
Results have been obtained for supersonic 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 |
Oscillating supersonic delta wing with straight leading edges |
| title_short |
Oscillating supersonic delta wing with straight leading edges |
| title_full |
Oscillating supersonic delta wing with straight leading edges |
| title_fullStr |
Oscillating supersonic delta wing with straight leading edges |
| title_full_unstemmed |
Oscillating supersonic delta wing with straight leading edges |
| title_sort |
oscillating supersonic delta wing with straight leading edges |
| publisher |
IJCER |
| publishDate |
2012 |
| url |
http://irep.iium.edu.my/49942/ http://irep.iium.edu.my/49942/ http://irep.iium.edu.my/49942/1/JO2512261233-print-paper8.pdf |
| first_indexed |
2023-09-18T21:10:34Z |
| last_indexed |
2023-09-18T21:10:34Z |
| _version_ |
1777411225023414272 |