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| Main Authors: | , , , , |
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| Format: | Recurso digital |
| Language: | |
| Published: |
Zenodo
2025
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| Online Access: | https://doi.org/10.5281/zenodo.18073226 |
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Table of 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.