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<p>The evolution of unmanned aerial vehicle (UAV) systems continues to accelerate due to the integration of advanced simulation environments that enable rapid design iteration and aerodynamic optimization. This study presents a parametric investigation into the influence of empennage configuration—specifically cant tail angle and vertical tailplane height—on the aerodynamic performance of fixed-wing UAVs. A total of thirty-six full-scale three-dimensional UAV models were developed using SOLIDWORKS, each utilizing the SD8020 airfoil for both the main and tail wings. The models incorporate combinations of three cant angles (30°, 45°, 60°), three tail heights (1.0&#xa0;m, 1.5&#xa0;m, 2.0&#xa0;m), and four angles of attack (2°, 3°, 4°, 5°). High-fidelity aerodynamic analysis was conducted using steady-state Reynolds-averaged Navier–Stokes (RANS) simulations with the SST k–ω turbulence model in ANSYS Fluent. The results reveal that the configuration with a cant angle of 60°, tail height of 1.0&#xa0;m, and angle of attack of 4° yielded the highest aerodynamic efficiency, exhibiting a 39% improvement in lift-to-drag ratio compared to the lowest-performing configuration. The findings provide actionable insight for UAV tail architecture design, supporting more efficient performance-driven development of autonomous aerial platforms.</p>

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Parametric aerodynamic characterization of tail geometry variations in fixed-wing UAVs

  • 期刊论文

  • 发表日期：

    2025年9月24日

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  • Ali J. Dawood Al-Khafaji,
  • Luttfi A. Al-Haddad

摘要

The evolution of unmanned aerial vehicle (UAV) systems continues to accelerate due to the integration of advanced simulation environments that enable rapid design iteration and aerodynamic optimization. This study presents a parametric investigation into the influence of empennage configuration—specifically cant tail angle and vertical tailplane height—on the aerodynamic performance of fixed-wing UAVs. A total of thirty-six full-scale three-dimensional UAV models were developed using SOLIDWORKS, each utilizing the SD8020 airfoil for both the main and tail wings. The models incorporate combinations of three cant angles (30°, 45°, 60°), three tail heights (1.0 m, 1.5 m, 2.0 m), and four angles of attack (2°, 3°, 4°, 5°). High-fidelity aerodynamic analysis was conducted using steady-state Reynolds-averaged Navier–Stokes (RANS) simulations with the SST k–ω turbulence model in ANSYS Fluent. The results reveal that the configuration with a cant angle of 60°, tail height of 1.0 m, and angle of attack of 4° yielded the highest aerodynamic efficiency, exhibiting a 39% improvement in lift-to-drag ratio compared to the lowest-performing configuration. The findings provide actionable insight for UAV tail architecture design, supporting more efficient performance-driven development of autonomous aerial platforms.