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<p>Trailing-edge truncation (TET) on an airfoil is a practical geometric modification commonly adopted in propeller and rotor blade design to improve structural durability and manufacturability. Previous studies have reported that TET applied to thick airfoils can yield aerodynamic performance improvements, particularly at high angles of attack. However, such results are often based on comparisons with other airfoils of similar thickness ratios rather than with the original unmodified geometry. In contrast, for thin airfoils, most existing analyses have focused on blunt trailing-edge configurations achieved by increasing the airfoil thickness near the trailing edge, rather than by directly truncating the trailing edge. In this study, the aerodynamic behavior of two thin NACA 16-series airfoils—NACA 16-209 and NACA 16-315—was investigated for various truncation ratios through steady Reynolds-Averaged Navier–Stokes (RANS) simulations using the SST k–ω turbulence model. The findings show that moderate truncation can enhance aerodynamic efficiency by improving base pressure recovery and stabilizing the wake. For NACA 16-209, truncations up to 5% of the chord increased the lift-to-drag ratio by more than 20%, primarily due to reduced pressure drag, while the lift characteristics remained nearly unchanged. In the thicker NACA 16-315 airfoil, the maximum efficiency improvement occurred at 97.5%-chord truncation, yielding up to 20% increase in <i>L/D</i> at 6° angle of attack. However, deeper truncation led to significant drag penalties, and the 90%-chord configuration exhibited up to 20% reduction in aerodynamic efficiency despite moderate lift gains.</p>

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Numerical Study on the Performance of Thin NACA Airfoils with Moderately Truncated Trailing Edges

  • 期刊论文

  • 发表日期：

    2026年4月29日

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  • Hojun Jang,
  • Byoungsoo Kim

摘要

Trailing-edge truncation (TET) on an airfoil is a practical geometric modification commonly adopted in propeller and rotor blade design to improve structural durability and manufacturability. Previous studies have reported that TET applied to thick airfoils can yield aerodynamic performance improvements, particularly at high angles of attack. However, such results are often based on comparisons with other airfoils of similar thickness ratios rather than with the original unmodified geometry. In contrast, for thin airfoils, most existing analyses have focused on blunt trailing-edge configurations achieved by increasing the airfoil thickness near the trailing edge, rather than by directly truncating the trailing edge. In this study, the aerodynamic behavior of two thin NACA 16-series airfoils—NACA 16-209 and NACA 16-315—was investigated for various truncation ratios through steady Reynolds-Averaged Navier–Stokes (RANS) simulations using the SST k–ω turbulence model. The findings show that moderate truncation can enhance aerodynamic efficiency by improving base pressure recovery and stabilizing the wake. For NACA 16-209, truncations up to 5% of the chord increased the lift-to-drag ratio by more than 20%, primarily due to reduced pressure drag, while the lift characteristics remained nearly unchanged. In the thicker NACA 16-315 airfoil, the maximum efficiency improvement occurred at 97.5%-chord truncation, yielding up to 20% increase in L/D at 6° angle of attack. However, deeper truncation led to significant drag penalties, and the 90%-chord configuration exhibited up to 20% reduction in aerodynamic efficiency despite moderate lift gains.