Estimation of stability derivatives of a delta wing in hypersonic flow
In the present study supersonic similitude has been used to obtain stability derivatives in pitch and roll of a delta wing for attached shock case. A strip theory is used in which strips at different span wise locations are independent. This combines with similitude to give a piston theory. The pres...
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| Format: | Article |
| Language: | English |
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RS Publication
2012
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| Online Access: | http://irep.iium.edu.my/49933/ http://irep.iium.edu.my/49933/1/52-paper7.pdf |
| _version_ | 1848783544924504064 |
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| author | Crasta, Asha Baig, Maugal Ahmed Ali Khan, Sher Afghan |
| author_facet | Crasta, Asha Baig, Maugal Ahmed Ali Khan, Sher Afghan |
| author_sort | Crasta, Asha |
| building | IIUM Repository |
| collection | Online Access |
| description | In the present study supersonic similitude has been used to obtain stability derivatives in pitch and roll of a delta wing for attached shock case. A strip theory is used in which strips at different span wise locations are independent. This combines with similitude to give a piston theory. The present theory is valid for attached shock case. Effects of wave reflections 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 & Hiu (1977). Results have been obtained for hypersonic flow of perfect case over a wide range of Mach number, incidences and sweep angles. A good agreement is obtained with Hui et al in some special cases. |
| first_indexed | 2025-11-14T16:23:03Z |
| format | Article |
| id | iium-49933 |
| institution | International Islamic University Malaysia |
| institution_category | Local University |
| language | English |
| last_indexed | 2025-11-14T16:23:03Z |
| publishDate | 2012 |
| publisher | RS Publication |
| recordtype | eprints |
| repository_type | Digital Repository |
| spelling | iium-499332016-07-18T02:09:54Z http://irep.iium.edu.my/49933/ Estimation of stability derivatives of a delta wing in hypersonic flow Crasta, Asha Baig, Maugal Ahmed Ali Khan, Sher Afghan TL Motor vehicles. Aeronautics. Astronautics TL787 Astronautics In the present study supersonic similitude has been used to obtain stability derivatives in pitch and roll of a delta wing for attached shock case. A strip theory is used in which strips at different span wise locations are independent. This combines with similitude to give a piston theory. The present theory is valid for attached shock case. Effects of wave reflections 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 & Hiu (1977). Results have been obtained for hypersonic flow of perfect case over a wide range of Mach number, incidences and sweep angles. A good agreement is obtained with Hui et al in some special cases. RS Publication 2012-09 Article PeerReviewed application/pdf en http://irep.iium.edu.my/49933/1/52-paper7.pdf Crasta, Asha and Baig, Maugal Ahmed Ali and Khan, Sher Afghan (2012) Estimation of stability derivatives of a delta wing in hypersonic flow. International Journal of Emerging trends in Engineering and Development (IJETED), 6 (2). pp. 505-516. ISSN 2249-6149 http://www.rspublication.com/ijeted/ijeted_index.htm |
| spellingShingle | TL Motor vehicles. Aeronautics. Astronautics TL787 Astronautics Crasta, Asha Baig, Maugal Ahmed Ali Khan, Sher Afghan Estimation of stability derivatives of a delta wing in hypersonic flow |
| title | Estimation of stability derivatives of a delta wing in hypersonic flow |
| title_full | Estimation of stability derivatives of a delta wing in hypersonic flow |
| title_fullStr | Estimation of stability derivatives of a delta wing in hypersonic flow |
| title_full_unstemmed | Estimation of stability derivatives of a delta wing in hypersonic flow |
| title_short | Estimation of stability derivatives of a delta wing in hypersonic flow |
| title_sort | estimation of stability derivatives of a delta wing in hypersonic flow |
| topic | TL Motor vehicles. Aeronautics. Astronautics TL787 Astronautics |
| url | http://irep.iium.edu.my/49933/ http://irep.iium.edu.my/49933/ http://irep.iium.edu.my/49933/1/52-paper7.pdf |