Computational Assessment of Drag Behavior for Spiked Light Assault Missile.

Document Type : Original Article

Authors

1 M.Sc. Student, Aerospace Engineering Department, Military Technical College, Egypt.

2 Ph.D., Senior lecturer at Aerospace Engineering Department, Military Technical College, Egypt.

3 Professor, Aerospace Engineering Department, Military Technical College, Egypt.

10.1088/1742-6596/2616/1//asat.2025.453557

Abstract

This paper presents a comprehensive numerical analysis of the aerodynamic behaviour of a spiked light missile designed for supersonic flight. The study focuses on the impact of a forebody-mounted spike on drag reduction and shock wave mitigation at speeds up to Mach 2.5. Utilizing a 3D, double-precision, pressure-based solver and the Shear Stress Transport (SST) k-ω turbulence model, the simulations accurately capture boundary layer separation and shock-wave interactions, essential for high-speed aerodynamic assessments. The computational domain is carefully defined to encompass the detached shock wave system generated by the missile's blunt nose and spike, ensuring that all relevant flow phenomena are analysed. The results indicate that the spike design significantly alters the pressure distribution on the missile's forebody, leading to a notable reduction in drag. The findings underscore the importance of aerodynamic drag reduction techniques in improving the performance and fuel efficiency of high-speed vehicles, contributing valuable insights to the field of aerospace engineering.
International Conference on Aerospace Sciences and Aviation Technology
Volume 21, Issue 21
21st International Conference on Aerospace Sciences & Aviation Technology, ASAT 21, 2025.
September 2025
Pages 1-9

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