Analysis of flow characteristics around sharp, blunt, and bulb-shaped missile nose geometries

Shetty, Shamitha and Nagarkar, Kavana and Khan, Sher Afghan and Aabid, Abdul and Baig, Muneer (2025) Analysis of flow characteristics around sharp, blunt, and bulb-shaped missile nose geometries. International Journal of Thermofluids, 28. pp. 1-13. ISSN 2666-2027

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Abstract

The current study investigates the aerodynamic characteristics of three distinct missile nose cone geometries: sharp, blunt, and bulb-shaped under supersonic conditions at Mach numbers 2.4, 2.8, 3.2, and 3.6. The primary objective is to analyze key parameters, such as lift and drag coefficients, and compare the findings with values reported in existing literature. The research aims to explore the flow physics responsible for variations in drag force as the missile's nose shape is altered. Supersonic missile design has drawn significant interest, with improving performance remaining a critical focus for researchers and engineers. One of the main challenges in achieving better performance is mitigating the high drag forces experienced at these speeds. The research employs two-dimensional computational fluid dynamics simulations using the standard k-epsilon turbulence model In ANSYS Fluent. Key parameters such as drag coefficient, lift coefficient, and pressure distribution are analyzed to understand the impact of nose shape on aerodynamic efficiency. Results indicate that the sharp nose geometry exhibits significantly reduced drag compared to the blunt and bulb configurations due to streamlined shock wave interactions and reduced pressure concentration at the nose tip. Conversely, while producing higher drag, the blunt shape offers better heat dissipation potential due to increased surface exposure. This study fills a gap in the literature by conducting a detailed comparative analysis of unconventional nose shapes at high Mach numbers. The findings contribute to improved missile nose design by balancing drag reduction and thermal management in high-speed flight regimes. The study concludes that minimizing the missile’s exposed surface area to the freestream and shock interactions effectively reduces drag, as smaller surface areas diminish shock interaction and associated drag forces.

Item Type:	Article (Journal)
Uncontrolled Keywords:	Computational fluid dynamics (CFD), Supersonic flow, Nose cone geometry, Shock wave interaction, Missile aerodynamics, Drag reduction
Subjects:	T Technology > TL Motor vehicles. Aeronautics. Astronautics > TL780 Rockets
Kulliyyahs/Centres/Divisions/Institutes (Can select more than one option. Press CONTROL button):	Kulliyyah of Engineering > Department of Mechanical Engineering Kulliyyah of Engineering
Depositing User:	Prof. Dr. Sher Afghan Khan
Date Deposited:	02 Jul 2025 09:29
Last Modified:	02 Jul 2025 09:29
URI:	http://irep.iium.edu.my/id/eprint/121818

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