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Zenodo
2025
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| Online-Zugang: | https://doi.org/10.5281/zenodo.18073226 |
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| author | Mrs. Lukkani Sushma Kanthala Saidhar Kamarajugadda Dinesh Kumar Paladi Sai Balaji Harshitha Joshi |
| author_facet | Mrs. Lukkani Sushma Kanthala Saidhar Kamarajugadda Dinesh Kumar Paladi Sai Balaji Harshitha Joshi |
| contents | This study investigates the aerodynamic performance of different nose cone designs for supersonic aircraft applications using Computational Fluid Dynamics (CFD). Three nose cone geometriesconical, tangent ogive, and parabolicwere analyzed at Mach 3 across four fineness ratios (L/D = 1.5, 2.5, 3.5, 4.5) using ANSYS Fluent software. A mesh independence study confirmed solution accuracy with drag force variation below 0.01% upon refinement. The results show that increasing fineness ratio reduces drag significantly for all shapes, with the conical nose achieving the lowest drag coefficient (Cd = 0.251) at L/D=4.5. The parabolic shape performed best at moderate lengths (L/D=2.5, Cd=0.361). The study concludes that while nose cone shape is important, the fineness ratio is a critical parameter for drag optimization in supersonic flight. These findings provide practical insights for aircraft designers seeking to minimize aerodynamic resistance in high-speed applications. |
| format | Recurso digital |
| id | zenodo_https___doi_org_10_5281_zenodo_18073226 |
| institution | Zenodo |
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| publishDate | 2025 |
| publisher | Zenodo |
| record_format | zenodo |
| spellingShingle | CFD Analysis and Comparison of Supersonic Aircraft Nose Cone Designs for Drag Reduction Mrs. Lukkani Sushma Kanthala Saidhar Kamarajugadda Dinesh Kumar Paladi Sai Balaji Harshitha Joshi This study investigates the aerodynamic performance of different nose cone designs for supersonic aircraft applications using Computational Fluid Dynamics (CFD). Three nose cone geometriesconical, tangent ogive, and parabolicwere analyzed at Mach 3 across four fineness ratios (L/D = 1.5, 2.5, 3.5, 4.5) using ANSYS Fluent software. A mesh independence study confirmed solution accuracy with drag force variation below 0.01% upon refinement. The results show that increasing fineness ratio reduces drag significantly for all shapes, with the conical nose achieving the lowest drag coefficient (Cd = 0.251) at L/D=4.5. The parabolic shape performed best at moderate lengths (L/D=2.5, Cd=0.361). The study concludes that while nose cone shape is important, the fineness ratio is a critical parameter for drag optimization in supersonic flight. These findings provide practical insights for aircraft designers seeking to minimize aerodynamic resistance in high-speed applications. |
| title | CFD Analysis and Comparison of Supersonic Aircraft Nose Cone Designs for Drag Reduction |
| url | https://doi.org/10.5281/zenodo.18073226 |