Analysis of damping derivatives for delta wings in hypersonic flow for curved leading edges with full sine wave
In this study, an attempt is made to evaluate the effect of first arched ends on the damping derived due to the pitch rate aimed at the variable sine wave bounty, flow deflection angle δ, pivot position, and the Mach numbers. Results show that with the escalation in the bounty of the complete sine w...
| Main Authors: | , , , |
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| Format: | Article |
| Language: | English English |
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Blue Eyes Intelligence Engineering & Sciences Publication
2019
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| Online Access: | http://irep.iium.edu.my/75893/ http://irep.iium.edu.my/75893/1/Renita-paper.pdf http://irep.iium.edu.my/75893/7/75893_Analysis%20of%20Damping%20Derivatives%20for%20Delta%20Wings_Scopus.pdf |
| _version_ | 1848788201157689344 |
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| author | Renita, sharon Monis Crasta, Asha Faheem, Mohammed Khan, Sher Afghan |
| author_facet | Renita, sharon Monis Crasta, Asha Faheem, Mohammed Khan, Sher Afghan |
| author_sort | Renita, sharon Monis |
| building | IIUM Repository |
| collection | Online Access |
| description | In this study, an attempt is made to evaluate the effect of first arched ends on the damping derived due to the pitch rate aimed at the variable sine wave bounty, flow deflection angle δ, pivot position, and the Mach numbers. Results show that with the escalation in the bounty of the complete sine wave (i.e., positive amplitude) there is an enlightened escalation in the pitch damping derivatives from h = 0, later in the downstream in the route of the sprawling verge it decreases till the location of the center of pressure and vice versa. At the location where the reasonable force acts, when we consider the stability derivatives in damping for the rate of pitch q, there is a rise in the numerical tenets of the spinoffs. This increase is non-linear in nature and not like for position near the leading edges. The level of the stifling derivatives owing to variations in Mach numbers, flow bend approach δ, and generosity of the sine wave remained in the same range. |
| first_indexed | 2025-11-14T17:37:03Z |
| format | Article |
| id | iium-75893 |
| institution | International Islamic University Malaysia |
| institution_category | Local University |
| language | English English |
| last_indexed | 2025-11-14T17:37:03Z |
| publishDate | 2019 |
| publisher | Blue Eyes Intelligence Engineering & Sciences Publication |
| recordtype | eprints |
| repository_type | Digital Repository |
| spelling | iium-758932019-12-04T05:21:28Z http://irep.iium.edu.my/75893/ Analysis of damping derivatives for delta wings in hypersonic flow for curved leading edges with full sine wave Renita, sharon Monis Crasta, Asha Faheem, Mohammed Khan, Sher Afghan QA297 Numerical Analysis In this study, an attempt is made to evaluate the effect of first arched ends on the damping derived due to the pitch rate aimed at the variable sine wave bounty, flow deflection angle δ, pivot position, and the Mach numbers. Results show that with the escalation in the bounty of the complete sine wave (i.e., positive amplitude) there is an enlightened escalation in the pitch damping derivatives from h = 0, later in the downstream in the route of the sprawling verge it decreases till the location of the center of pressure and vice versa. At the location where the reasonable force acts, when we consider the stability derivatives in damping for the rate of pitch q, there is a rise in the numerical tenets of the spinoffs. This increase is non-linear in nature and not like for position near the leading edges. The level of the stifling derivatives owing to variations in Mach numbers, flow bend approach δ, and generosity of the sine wave remained in the same range. Blue Eyes Intelligence Engineering & Sciences Publication 2019-10 Article PeerReviewed application/pdf en http://irep.iium.edu.my/75893/1/Renita-paper.pdf application/pdf en http://irep.iium.edu.my/75893/7/75893_Analysis%20of%20Damping%20Derivatives%20for%20Delta%20Wings_Scopus.pdf Renita, sharon Monis and Crasta, Asha and Faheem, Mohammed and Khan, Sher Afghan (2019) Analysis of damping derivatives for delta wings in hypersonic flow for curved leading edges with full sine wave. International Journal of Engineering and Advanced Technology (IJEAT), 9 (1). pp. 5457-5466. ISSN 2249-8958 https://www.ijeat.org 10.35940/ijeat.A3085.109119 |
| spellingShingle | QA297 Numerical Analysis Renita, sharon Monis Crasta, Asha Faheem, Mohammed Khan, Sher Afghan Analysis of damping derivatives for delta wings in hypersonic flow for curved leading edges with full sine wave |
| title | Analysis of damping derivatives for delta wings in hypersonic flow for curved leading edges with full sine wave |
| title_full | Analysis of damping derivatives for delta wings in hypersonic flow for curved leading edges with full sine wave |
| title_fullStr | Analysis of damping derivatives for delta wings in hypersonic flow for curved leading edges with full sine wave |
| title_full_unstemmed | Analysis of damping derivatives for delta wings in hypersonic flow for curved leading edges with full sine wave |
| title_short | Analysis of damping derivatives for delta wings in hypersonic flow for curved leading edges with full sine wave |
| title_sort | analysis of damping derivatives for delta wings in hypersonic flow for curved leading edges with full sine wave |
| topic | QA297 Numerical Analysis |
| url | http://irep.iium.edu.my/75893/ http://irep.iium.edu.my/75893/ http://irep.iium.edu.my/75893/ http://irep.iium.edu.my/75893/1/Renita-paper.pdf http://irep.iium.edu.my/75893/7/75893_Analysis%20of%20Damping%20Derivatives%20for%20Delta%20Wings_Scopus.pdf |