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<p>The performance of the existing propeller of a High-Altitude Long Endurance (HALE) UAV requires improvement to operate efficiently at 60,000 ft, where air density and Reynolds numbers are reduced. This study develops an improved propeller geometry featuring optimized chord and twist distributions with high surface curvature tailored for high-altitude flight. A gradient-based optimization approach, Sequential Least Squares Programming (SLSQP), is employed to explore the design space due to its ability to achieve accurate solutions with less computational time. To accommodate the large number of evaluations required by the optimizer, a rapid aerodynamic analysis based on Blade Element Momentum Theory (BEMT) is integrated into the design loop. The optimized geometry is subsequently validated using a higher-fidelity Reynolds-Averaged Navier–Stokes (RANS) CFD solver under both on-design and off-design conditions. The optimized design achieves a propeller efficiency of 60.4%, representing a 3.4% improvement over the baseline configuration. The close agreement between BEMT and CFD results confirms that the proposed optimization framework can produce reliable high-altitude propeller designs with reduced computational cost. </p>

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Design optimization of HALE propeller by using SLSQP method

  • 期刊论文

  • 出版模式：

    开放获取

  • 发表日期：

    2026年1月23日

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  • Mochammad Agoes Moelyadi,
  • Ema Amalia,
  • Angka Bayu Putranto,
  • I. Nengah Diasta,
  • Muhammad Lucky Witjaksono,
  • Faris Muhammad Tsaqif,
  • Syahrahman Akhdiyatullah Ginting

摘要

The performance of the existing propeller of a High-Altitude Long Endurance (HALE) UAV requires improvement to operate efficiently at 60,000 ft, where air density and Reynolds numbers are reduced. This study develops an improved propeller geometry featuring optimized chord and twist distributions with high surface curvature tailored for high-altitude flight. A gradient-based optimization approach, Sequential Least Squares Programming (SLSQP), is employed to explore the design space due to its ability to achieve accurate solutions with less computational time. To accommodate the large number of evaluations required by the optimizer, a rapid aerodynamic analysis based on Blade Element Momentum Theory (BEMT) is integrated into the design loop. The optimized geometry is subsequently validated using a higher-fidelity Reynolds-Averaged Navier–Stokes (RANS) CFD solver under both on-design and off-design conditions. The optimized design achieves a propeller efficiency of 60.4%, representing a 3.4% improvement over the baseline configuration. The close agreement between BEMT and CFD results confirms that the proposed optimization framework can produce reliable high-altitude propeller designs with reduced computational cost.