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<p>This research investigates the aerodynamic effects of a forward-positioned spike attached to a hemispherical body in high-speed flows, aiming to understand its impact on drag reduction and heat flux mitigation. Axisymmetric compressible laminar Averaged Navier–Stokes equations are employed, utilizing finite volume discretization and a k-omega turbulence modelling method. Numerical assessments are conducted at Mach 6 and zero angle of attack, analysing variations in spike length, shape, and nose configuration. A mesh independence study is performed by comparing different coefficients of drag and local pressure coefficients at various mesh resolutions and the results are validated against experimental data. The results demonstrate that spike geometry significantly influences drag reduction and heat flow mitigation by altering shock structures, separation zones, and reattachment locations. Enhancing the spike’s size and configuration optimizes the conical recirculation zone, hence reducing aerodynamic drag and surface thermal effects. The hemispherical aerodisk configuration generates a distinctive shock pattern that modifies the flow field behind the spike, while the flat aerodisk results in an alternative shock interaction. Excessive spike extension may influence these outcomes due to potentially unstable interactions. These findings facilitate the optimization of spike designs for high-speed vehicle applications, improving aerodynamic efficiency and thermal protection.</p>

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Computational Investigation of Aerothermodynamic Characteristics of Spherical and Flat Disc Spiked Blunt Body at Hypersonic Flow

  • 期刊论文

  • 发表日期：

    2025年4月29日

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  • Balaji Ravi,
  • Bereket Kassaye Oda,
  • Amit Kumar Thakur,
  • Anita Gehlot

摘要

This research investigates the aerodynamic effects of a forward-positioned spike attached to a hemispherical body in high-speed flows, aiming to understand its impact on drag reduction and heat flux mitigation. Axisymmetric compressible laminar Averaged Navier–Stokes equations are employed, utilizing finite volume discretization and a k-omega turbulence modelling method. Numerical assessments are conducted at Mach 6 and zero angle of attack, analysing variations in spike length, shape, and nose configuration. A mesh independence study is performed by comparing different coefficients of drag and local pressure coefficients at various mesh resolutions and the results are validated against experimental data. The results demonstrate that spike geometry significantly influences drag reduction and heat flow mitigation by altering shock structures, separation zones, and reattachment locations. Enhancing the spike’s size and configuration optimizes the conical recirculation zone, hence reducing aerodynamic drag and surface thermal effects. The hemispherical aerodisk configuration generates a distinctive shock pattern that modifies the flow field behind the spike, while the flat aerodisk results in an alternative shock interaction. Excessive spike extension may influence these outcomes due to potentially unstable interactions. These findings facilitate the optimization of spike designs for high-speed vehicle applications, improving aerodynamic efficiency and thermal protection.