Effect of angle of incidence on roll damping derivatives of a delta wing
In the Present paper effect of angle of incidence on roll damping derivative of a delta wing with curved leading edges with attached shock case has been studied. A Strip theory is used in which strips at different span wise location are independent of each other. This combines with similitude to giv...
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| Format: | Article |
| Language: | English |
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RS Publication
2014
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| Online Access: | http://irep.iium.edu.my/49937/ http://irep.iium.edu.my/49937/ http://irep.iium.edu.my/49937/1/effect_of_angle_of_incidence_on_rolling_moment_derivative-paper14.pdf |
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iium-49937 |
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iium-499372018-06-20T06:47:04Z http://irep.iium.edu.my/49937/ Effect of angle of incidence on roll damping derivatives of a delta wing Crasta, Asha Khan, Sher Afghan TL787 Astronautics In the Present paper effect of angle of incidence on roll damping derivative of a delta wing with curved leading edges with attached shock case has been studied. A Strip theory is used in which strips at different span wise location are independent of each other. This combines with similitude to give a piston theory. The Present theory is valid only when the shock wave is attached with the leading edge of the wing. Effects of secondary wave reflection and viscosity have not been taken into account. Effect of leading edge bluntness also has been neglected. Results have been obtained for hypersonic flow of perfect gases over a wide range of angle of attack and Mach number. RS Publication 2014-03 Article PeerReviewed application/pdf en http://irep.iium.edu.my/49937/1/effect_of_angle_of_incidence_on_rolling_moment_derivative-paper14.pdf Crasta, Asha and Khan, Sher Afghan (2014) Effect of angle of incidence on roll damping derivatives of a delta wing. International Journal of Emerging trends in Engineering and Development (IJETED), 4 (2). pp. 343-356. ISSN 2249-6149 http://www.rspublication.com/ijeted/2014/march14/34.pdf |
| repository_type |
Digital Repository |
| institution_category |
Local University |
| institution |
International Islamic University Malaysia |
| building |
IIUM Repository |
| collection |
Online Access |
| language |
English |
| topic |
TL787 Astronautics |
| spellingShingle |
TL787 Astronautics Crasta, Asha Khan, Sher Afghan Effect of angle of incidence on roll damping derivatives of a delta wing |
| description |
In the Present paper effect of angle of incidence on roll damping derivative of a delta wing with curved leading edges with attached shock case has been studied. A Strip theory is used in which strips at different span wise location are independent of each other. This combines with similitude to give a piston theory. The Present theory is valid only when the shock wave is attached with the leading edge of the wing. Effects of secondary wave reflection and viscosity have not been taken into account. Effect of leading edge bluntness also has been neglected. Results have been obtained for hypersonic flow of perfect gases over a wide range of angle of attack and Mach number. |
| format |
Article |
| author |
Crasta, Asha Khan, Sher Afghan |
| author_facet |
Crasta, Asha Khan, Sher Afghan |
| author_sort |
Crasta, Asha |
| title |
Effect of angle of incidence on roll damping derivatives of a delta wing |
| title_short |
Effect of angle of incidence on roll damping derivatives of a delta wing |
| title_full |
Effect of angle of incidence on roll damping derivatives of a delta wing |
| title_fullStr |
Effect of angle of incidence on roll damping derivatives of a delta wing |
| title_full_unstemmed |
Effect of angle of incidence on roll damping derivatives of a delta wing |
| title_sort |
effect of angle of incidence on roll damping derivatives of a delta wing |
| publisher |
RS Publication |
| publishDate |
2014 |
| url |
http://irep.iium.edu.my/49937/ http://irep.iium.edu.my/49937/ http://irep.iium.edu.my/49937/1/effect_of_angle_of_incidence_on_rolling_moment_derivative-paper14.pdf |
| first_indexed |
2023-09-18T21:10:34Z |
| last_indexed |
2023-09-18T21:10:34Z |
| _version_ |
1777411224440406016 |