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<p>By adopting the CFD based approach, the hypersonic flow nature is investigated under a Free-stream Mach number of 6 for two distinct re-entry configurations; namely, a spiked conical-nosed body, and a spiked T-shaped blunt-nosed body, each coupled with counterflow jets. A high-fidelity structured mesh and the SST k-omega Turbulence model within the Ansys Fluent framework are employed to capture flow phenomena like bow shock detachment, recirculation, and wake formation with finer precision. The analysis is performed on vital performance parameters such as aerodynamic drag, surface pressure and temperature distributions, and the effect of counterflow jets on shock stand-off distance and thermal load reduction. We find results indicating drag reduction of 52% by the conical blunt-nosed configuration compared to the T-Shape nose configuration and an increase in shock stand-off distance by 0.0175. Moreover, counterflow jets reduce the surface temperature by a maximum of 300&#xa0;K at critical forebody regions, while the total pressure recovery improves by 50%. These findings affirm that nose shape is a critical parameter influencing the hypersonic flow control and thus offers new perspectives for the design optimization, with T-shaped configuration providing improved thermal protection and aerodynamic efficiency.</p>

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Comparative analysis of hypersonic flow characteristics over spiked re-entry bodies with counterflow jets using CFD

  • 期刊论文

  • 发表日期：

    2025年9月15日

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  • Divij Arora,
  • Sachin Srivastava,
  • Suryaprakash Gairola

摘要

By adopting the CFD based approach, the hypersonic flow nature is investigated under a Free-stream Mach number of 6 for two distinct re-entry configurations; namely, a spiked conical-nosed body, and a spiked T-shaped blunt-nosed body, each coupled with counterflow jets. A high-fidelity structured mesh and the SST k-omega Turbulence model within the Ansys Fluent framework are employed to capture flow phenomena like bow shock detachment, recirculation, and wake formation with finer precision. The analysis is performed on vital performance parameters such as aerodynamic drag, surface pressure and temperature distributions, and the effect of counterflow jets on shock stand-off distance and thermal load reduction. We find results indicating drag reduction of 52% by the conical blunt-nosed configuration compared to the T-Shape nose configuration and an increase in shock stand-off distance by 0.0175. Moreover, counterflow jets reduce the surface temperature by a maximum of 300 K at critical forebody regions, while the total pressure recovery improves by 50%. These findings affirm that nose shape is a critical parameter influencing the hypersonic flow control and thus offers new perspectives for the design optimization, with T-shaped configuration providing improved thermal protection and aerodynamic efficiency.