Numerical Analysis of Aerodynamic Performance of Low Tip‑Speed Rotors with Gurney Flaps

WAN Haoyun; HAN Dong; WANG Tianjian

doi:10.16356/j.2097-6771.2026.02.003

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Numerical Analysis of Aerodynamic Performance of Low Tip‑Speed Rotors with Gurney Flaps

更新时间：2026-04-30

- Numerical Analysis of Aerodynamic Performance of Low Tip‑Speed Rotors with Gurney Flaps
- Journal of Nanjing University of Aeronautics & Astronautics（Natural Science Edition） Vol. 58, Issue 2, Pages: 277-284(2026)
- 作者机构：
  
  南京航空航天大学直升机动力学全国重点实验室/直升机研究院，南京 210016
- 作者简介：
- 基金信息：
- DOI：10.16356/j.2097-6771.2026.02.003
  CLC： V211.52
- Received：10 October 2025，
  
  Revised：2026-01-13，
  
  Published：28 April 2026
- 稿件说明：
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万浩云，韩东，王天健. 低桨尖速度旋翼加装格尼襟翼气动性能数值分析［J］. 南京航空航天大学学报（自然科学版），2026，58（2）：277⁃284.

WAN Haoyun， HAN Dong， WANG Tianjian. Numerical analysis of aerodynamic performance of low tip‑speed rotors with Gurney flaps［J］. Journal of Nanjing University of Aeronautics & Astronautics（Natural Science Edition），2026， 58（2）：277⁃284.
万浩云，韩东，王天健. 低桨尖速度旋翼加装格尼襟翼气动性能数值分析［J］. 南京航空航天大学学报（自然科学版），2026，58（2）：277⁃284. DOI： 10.16356/j.2097-6771.2026.02.003.

WAN Haoyun， HAN Dong， WANG Tianjian. Numerical analysis of aerodynamic performance of low tip‑speed rotors with Gurney flaps［J］. Journal of Nanjing University of Aeronautics & Astronautics（Natural Science Edition），2026， 58（2）：277⁃284. DOI： 10.16356/j.2097-6771.2026.02.003.

摘要

为探索提升低桨尖速度旋翼升力的可能性，建立旋翼性能计算模型，由UH‑60A直升机飞行试验数据验证了模型正确性，进一步研究格尼襟翼对低桨尖速度旋翼悬停及前飞性能的影响。结果表明：悬停时，格尼襟翼可提升低桨尖速度旋翼拉力，但伴随功率增加，拉力系数提升可达12.00%，对应功率系数增加7.98%。在大拉力状态，格尼襟翼可使旋翼在较低总距下维持与原基准旋翼相同的拉力，悬停效率显著提升18.55%。前飞100 km/h时，格尼襟翼拉力系数提升11.30%，但功率代价更高，对应功率系数增加18.64%。格尼襟翼可增大升阻比，升阻比提升可达28.77%。对于低桨尖速度旋翼，拉力一定时，格尼襟翼可减小迎角（Angle of attack， AoA），增大升阻比，提升大拉力状态的旋翼气动性能。

Abstract

To explore the potential for increasing lift on low tip-speed rotors， a rotor performance calculation model is established. The flight data of the UH-60A helicopter are utilized to validate this model. Further research is conducted on the influence of the Gurney flap on the hovering and forward flight performance of the low tip-speed rotor. The results indicate that， in hover， Gurney flaps increase rotor thrust but with higher power consumption. The thrust coefficient rises by up to 12.00%， while the power coefficient increases by 7.98%. Under high-thrust conditions， Gurney flaps enable the rotor to maintain the same thrust as the baseline configuration at a reduced collective pitch， thereby significantly improving the figure of merit by 18.55%. In forward flight （100 km/h）， the thrust coefficient improves by 11.30%， but with greater power penalty （power coefficient increases by 18.64%）. Gurney flaps also improve the lift-to-drag ratio， with a maximum increase of 28.77%. For low tip-speed rotors， at a given thrust， Gurney flaps reduce the angle of attack and increase the lift-to-drag ratio， thereby improving rotor aerodynamic performance in high-thrust conditions.

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references

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