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<p>Active and passive flow control methods are utilized to achieve two-dimensional trajectory correction for projectiles, facilitating the intelligent enhancement of conventional munitions. This study implements passive flow control by optimizing diversion groove geometry to leverage the aerodynamic properties of asymmetric flow fields for subsonic trajectory correction. Wind tunnel tests are conducted on both traditional and modified models featuring straight-wall grooves on the blunt nose. The investigation explores the effects of asymmetric flow fields induced by the diversion groove under varying conditions on aerodynamic performance. Numerical simulation results are analyzed to visualize complex flow phenomena. A divergent groove is introduced at the blunt nose, and its geometric parameters, including divergence angle and groove length, are varied in iterative numerical calculations. Key flow characteristics are identified, and the findings demonstrate that the divergent groove significantly enhances the aerodynamic performance of asymmetric flow fields. The optimal configuration, with a divergence angle of <i>γ</i> = 10° and a groove length of 45&#xa0;mm, results in an increase in the lift coefficient by 82% and the yaw force coefficient by 78%, compared to the straight-wall groove.</p>

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Aerodynamic Analysis and Geometric Optimization of Diversion Grooves in Blunt-Nose Corrected Projectiles

  • 期刊论文

  • 发表日期：

    2025年2月6日

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  • Angang Luo,
  • Qinkun Xiao,
  • Xing Liu,
  • Xinlu Si,
  • Wei Sun,
  • Lijun Zhang

摘要

Active and passive flow control methods are utilized to achieve two-dimensional trajectory correction for projectiles, facilitating the intelligent enhancement of conventional munitions. This study implements passive flow control by optimizing diversion groove geometry to leverage the aerodynamic properties of asymmetric flow fields for subsonic trajectory correction. Wind tunnel tests are conducted on both traditional and modified models featuring straight-wall grooves on the blunt nose. The investigation explores the effects of asymmetric flow fields induced by the diversion groove under varying conditions on aerodynamic performance. Numerical simulation results are analyzed to visualize complex flow phenomena. A divergent groove is introduced at the blunt nose, and its geometric parameters, including divergence angle and groove length, are varied in iterative numerical calculations. Key flow characteristics are identified, and the findings demonstrate that the divergent groove significantly enhances the aerodynamic performance of asymmetric flow fields. The optimal configuration, with a divergence angle of γ = 10° and a groove length of 45 mm, results in an increase in the lift coefficient by 82% and the yaw force coefficient by 78%, compared to the straight-wall groove.