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<p>At supersonic speeds, a drag-reducing aerospike is employed to lower the fore body pressure aerodynamic drag. As a result of the aerospike, the body is subjected to a detached shock. This area between the shock and the fore body creates an area of recirculated flow that reduces drag. This study investigates the aerodynamic performance characteristics of a missile equipped with an arrow-headed spike, utilizing ANSYS CFX software at a M = 2.5 and a zero-degree angle of attack (AoA). The axial force coefficient at the zero AoA was recorded as 0.91. The analysis revealed a complex system of oblique shocks, featuring symmetrical shock structures at zero degrees, and showed a significant reduction in the Mach number over the arrow-headed spike, surpassing 1 near the missile dome, indicating supersonic flow. The study’s results showed a maximum variation of 7.14% compared to existing CFD results and a 9% deviation from experimental data, validating the reliability of the computational model. These findings provide valuable insights into the aerodynamic behaviour of missile configurations with arrow-headed aerospikes and underscore the utility of computational fluid dynamics in aerospace vehicle design.</p>

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Conceptual Design and Aerodynamic Performance Analysis of a Missile with an Arrow-Headed Aerospike at Mach 2.5

  • 期刊论文

  • 发表日期：

    2026年2月14日

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  • V. Somashekar,
  • C. M. Vigneswaran,
  • Inamul Hasan

摘要

At supersonic speeds, a drag-reducing aerospike is employed to lower the fore body pressure aerodynamic drag. As a result of the aerospike, the body is subjected to a detached shock. This area between the shock and the fore body creates an area of recirculated flow that reduces drag. This study investigates the aerodynamic performance characteristics of a missile equipped with an arrow-headed spike, utilizing ANSYS CFX software at a M = 2.5 and a zero-degree angle of attack (AoA). The axial force coefficient at the zero AoA was recorded as 0.91. The analysis revealed a complex system of oblique shocks, featuring symmetrical shock structures at zero degrees, and showed a significant reduction in the Mach number over the arrow-headed spike, surpassing 1 near the missile dome, indicating supersonic flow. The study’s results showed a maximum variation of 7.14% compared to existing CFD results and a 9% deviation from experimental data, validating the reliability of the computational model. These findings provide valuable insights into the aerodynamic behaviour of missile configurations with arrow-headed aerospikes and underscore the utility of computational fluid dynamics in aerospace vehicle design.