Pitch and roll derivatives of a delta wing with curved leading edge in high speed flow
Ghosh's unified similitude has been applied to oscillating delta wings of arbitrary plan forms in supersonic/ hyper- sonic flow. The quasi-steady derivative which was obtained by Ghosh for a hypersonic delta wing is extended to supersonic Mach number and curved leading edges. The unsteady momen...
| Main Authors: | , , , |
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| Format: | Article |
| Language: | English |
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AerosocietyofIndia
1990
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| Subjects: | |
| Online Access: | http://irep.iium.edu.my/49889/ http://irep.iium.edu.my/49889/1/K-ghosh.pdf |
| _version_ | 1848783533465665536 |
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| author | Ghosh, K Murthy, M Khan, Sher Afghan Pandey, P K |
| author_facet | Ghosh, K Murthy, M Khan, Sher Afghan Pandey, P K |
| author_sort | Ghosh, K |
| building | IIUM Repository |
| collection | Online Access |
| description | Ghosh's unified similitude has been applied to oscillating delta wings of arbitrary plan forms in supersonic/ hyper- sonic flow. The quasi-steady derivative which was obtained by Ghosh for a hypersonic delta wing is extended to supersonic Mach number and curved leading edges. The unsteady moment derivative due to the incidence rate is obtained by combining Ghosh's unsteady theory and the quasi-steady theory. The results are compared with Hui et. al. The shock is assumed to be attached to the leading edge. The effects of viscosity and real gas have not been included. |
| first_indexed | 2025-11-14T16:22:52Z |
| format | Article |
| id | iium-49889 |
| institution | International Islamic University Malaysia |
| institution_category | Local University |
| language | English |
| last_indexed | 2025-11-14T16:22:52Z |
| publishDate | 1990 |
| publisher | AerosocietyofIndia |
| recordtype | eprints |
| repository_type | Digital Repository |
| spelling | iium-498892016-04-13T02:46:33Z http://irep.iium.edu.my/49889/ Pitch and roll derivatives of a delta wing with curved leading edge in high speed flow Ghosh, K Murthy, M Khan, Sher Afghan Pandey, P K TL500 Aeronautics Ghosh's unified similitude has been applied to oscillating delta wings of arbitrary plan forms in supersonic/ hyper- sonic flow. The quasi-steady derivative which was obtained by Ghosh for a hypersonic delta wing is extended to supersonic Mach number and curved leading edges. The unsteady moment derivative due to the incidence rate is obtained by combining Ghosh's unsteady theory and the quasi-steady theory. The results are compared with Hui et. al. The shock is assumed to be attached to the leading edge. The effects of viscosity and real gas have not been included. AerosocietyofIndia 1990-11 Article PeerReviewed application/pdf en http://irep.iium.edu.my/49889/1/K-ghosh.pdf Ghosh, K and Murthy, M and Khan, Sher Afghan and Pandey, P K (1990) Pitch and roll derivatives of a delta wing with curved leading edge in high speed flow. Aeronautical Society of India, 42 (4). pp. 299-302. ISSN 0972-950X http://www.aerosocietyindia.in |
| spellingShingle | TL500 Aeronautics Ghosh, K Murthy, M Khan, Sher Afghan Pandey, P K Pitch and roll derivatives of a delta wing with curved leading edge in high speed flow |
| title | Pitch and roll derivatives of a delta wing with curved leading edge in high speed flow |
| title_full | Pitch and roll derivatives of a delta wing with curved leading edge in high speed flow |
| title_fullStr | Pitch and roll derivatives of a delta wing with curved leading edge in high speed flow |
| title_full_unstemmed | Pitch and roll derivatives of a delta wing with curved leading edge in high speed flow |
| title_short | Pitch and roll derivatives of a delta wing with curved leading edge in high speed flow |
| title_sort | pitch and roll derivatives of a delta wing with curved leading edge in high speed flow |
| topic | TL500 Aeronautics |
| url | http://irep.iium.edu.my/49889/ http://irep.iium.edu.my/49889/ http://irep.iium.edu.my/49889/1/K-ghosh.pdf |