旋翼翼型俯仰沉浮耦合动态失速特性

吴家强; 李朗; 李国强; 谌俊丞; 余杰儒; 陈锐锋

doi:10.7638/kqdlxxb-2024.0112

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旋翼翼型俯仰沉浮耦合动态失速特性

研究论文 | 更新时间：2026-05-28

- 旋翼翼型俯仰沉浮耦合动态失速特性
- Dynamic stall characteristics of a rotor airfoil under coupled pitching-plunging motions
- 空气动力学学报 2025年43卷第11期页码：35-42
- 作者机构：
  
  1. 西南科技大学土木工程与建筑学院,绵阳,621010
  2. 空天飞行空气动力科学与技术全国重点实验室,绵阳,621000
- 作者简介：
  
  吴家强（2001—）, 男，四川成都人，硕士研究生，研究方向：旋翼空气动力学. E-mail：2602121287@qq.com
  李朗*（1979—）, 女，副教授，研究方向：高速空气动力学 E-mail：18845213@qq.com
- 基金信息：
  
  空天飞行空气动力科学与技术全国重点实验室基金（2023-YJKODL-F40301065）
- DOI：10.7638/kqdlxxb-2024.0112
  中图分类号： V211.52
- 纸质出版：2025
- 稿件说明：
移动端阅览
吴家强, 李朗, 李国强, 等. 旋翼翼型俯仰沉浮耦合动态失速特性[J]. 空气动力学学报, 2025, 43(11): 35−42.

WU Jiaqiang, LI Lang, LI Guoqiang, et al. Dynamic stall characteristics of a rotor airfoil under coupled pitching-plunging motions[J]. 2025, 43(11): 35-42.
吴家强, 李朗, 李国强, 等. 旋翼翼型俯仰沉浮耦合动态失速特性[J]. 空气动力学学报, 2025, 43(11): 35−42. DOI： 10.7638/kqdlxxb-2024.0112

WU Jiaqiang, LI Lang, LI Guoqiang, et al. Dynamic stall characteristics of a rotor airfoil under coupled pitching-plunging motions[J]. 2025, 43(11): 35-42. DOI： 10.7638/kqdlxxb-2024.0112.

摘要

直升机旋翼在实际飞行过程中，不仅经历周期性的俯仰振荡，还伴随上下沉浮运动，这加剧了流场结构和动态失速特性的复杂性。为研究高雷诺数旋翼多自由度振荡气动特性及失速机理，选取NACA 0015旋翼翼型为研究对象，采用运动嵌套网格及Realizable

k-ε

湍流模型，对雷诺数为2.0 × 10

的俯仰沉浮耦合运动进行数值模拟，并进一步分析相位角对动态失速特性的影响。结果表明：旋翼下沉运动是翼型产生升力的主要阶段。高雷诺数条件下，当沉浮振幅增至$ {h_{{\mathrm{m}}}} $ = 150 mm时，单纯沉浮运动会产生推力。上浮运动时，翼型会产生更大阻力，从而使耦合运动阻力系数整体增加，而翼型下沉运动时则相反；相位角$ \varphi = \mathrm{{\text{π}} }/2 $时，有效迎角（俯仰角和沉浮运动引起的诱导角的线性组合）的增加推迟升力失速角约1°，但阻力系数峰值较纯俯仰状态增加了56.9%。沉浮运动主要影响了上翼面分离区发展，以及不同尺度、频域动态涡结构的演变和相互作用程度，从而导致了耦合运动的气动力曲线和俯仰负行程脉动程度出现差异。

Abstract

The blade of a helicopter rotor encounters plunging motion in addition to periodic pitching oscillations during actual flight

which complicates the flow field structure and dynamic stall characteristics. The NACA 0015 rotor airfoil is selected as the study subject to examine the aerodynamic properties and stall mechanisms of multi-degree-of-freedom oscillations in a high-Reynolds-number rotor. The pitching-plunging coupled motion at a Reynolds number of 2.0×10

is simulated using the Real

izable

turbulence model with a moving overset grid. Additional analysis is conducted on how the phase angle between pitching and plunging motions affects the dynamic stall characteristics.The results indicate that the downward motion is the primary phase during which the airfoil generates lift. Under high-Reynolds-number conditions

increasing the plunging amplitude to 150 mm allows the pure plunging motion to produce thrust. During upward movement

the airfoil encounters greater drag

raising the coupled motion's overall drag coefficient. The opposite effect is seen during the downward movement. At a phase angle of

= π/2

the increase in the effective angle of attack (a combination of the pitching angle and the induced angle from the plunging motion) delays the lift stall angle by approximately 1°. However

the peak value of the drag coefficient increases by 56.9% compared with the pure pitching state.The plunging motion significantly impacts the development of the separation zone on the airfoil's upper surface

as well as the evolution and interaction of dynamic vortex structures across different scales and frequency domains. These effects result in differences in the aerodynamic force curves of the coupled motion and amplify the fluctuations during the negative pitch stroke.

关键词

Keywords

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