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<p>This extended study investigates the aerodynamic characteristics of a supersonic missile equipped with grid fins of varying spanwise sweep angles, using high-fidelity Computational Fluid Dynamics (CFD) simulations via the HiFUN solver. It builds upon our earlier work (Arul et al. in J Aeronaut Astronaut Aviat 57(5):1143–1170, 2025. 10.6125/JoAAA.202505_57(5)), where only the 30° swept-back grid fin configuration was analyzed. The objective of the current study is to evaluate the influence of sweep angle on aerodynamic performance by analysing drag reduction, lift characteristics, and stability across five swept-back configurations—10°, 20°, 30°, 40°, and 50°—in comparison to the baseline grid fin. Simulations were conducted at Mach numbers 1.8, 2.5, and 3.5 for angles of attack ranging from 0° to 15°. The results demonstrate that the swept-back fins significantly reduce the axial force coefficient (C<sub>A</sub>), achieving drag reduction between 5.6 and 12.7% depending on sweep angle and Mach number. Optimal aerodynamic performance was observed around 30°, where improved lift-to-drag ratio and pitching moment behaviour were recorded. While higher sweep angles (40°–50°) further decreased drag, a slight reduction in lift and stability was noted, indicating diminishing returns. The findings confirm that spanwise sweepback is an effective strategy for enhancing missile aerodynamic efficiency and control authority, with 30° identified as the most balanced configuration. This extended analysis offers refined design insights for optimizing grid fins in high-speed missile applications.</p>

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An extended parametric CFD study of supersonic missile grid fins with varying sweep angles using HiFUN solver

  • 期刊论文

  • 发表日期：

    2026年1月28日

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  • Mohana Pratheep Arul,
  • Suresh Chinnasamy,
  • Paramaguru Venugopal,
  • J. Siva,
  • S. Yaknesh,
  • N. Rajamurugu

摘要

This extended study investigates the aerodynamic characteristics of a supersonic missile equipped with grid fins of varying spanwise sweep angles, using high-fidelity Computational Fluid Dynamics (CFD) simulations via the HiFUN solver. It builds upon our earlier work (Arul et al. in J Aeronaut Astronaut Aviat 57(5):1143–1170, 2025. 10.6125/JoAAA.202505_57(5)), where only the 30° swept-back grid fin configuration was analyzed. The objective of the current study is to evaluate the influence of sweep angle on aerodynamic performance by analysing drag reduction, lift characteristics, and stability across five swept-back configurations—10°, 20°, 30°, 40°, and 50°—in comparison to the baseline grid fin. Simulations were conducted at Mach numbers 1.8, 2.5, and 3.5 for angles of attack ranging from 0° to 15°. The results demonstrate that the swept-back fins significantly reduce the axial force coefficient (CA), achieving drag reduction between 5.6 and 12.7% depending on sweep angle and Mach number. Optimal aerodynamic performance was observed around 30°, where improved lift-to-drag ratio and pitching moment behaviour were recorded. While higher sweep angles (40°–50°) further decreased drag, a slight reduction in lift and stability was noted, indicating diminishing returns. The findings confirm that spanwise sweepback is an effective strategy for enhancing missile aerodynamic efficiency and control authority, with 30° identified as the most balanced configuration. This extended analysis offers refined design insights for optimizing grid fins in high-speed missile applications.