Research on the hysteresis properties of a pitching NACA0012 airfoil under low transonic ground effect

LUO Xingdong; HOU Zihao

doi:10.7638/kqdlxxb-2024.0082

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Research on the hysteresis properties of a pitching NACA0012 airfoil under low transonic ground effect

更新时间：2026-05-28

- Research on the hysteresis properties of a pitching NACA0012 airfoil under low transonic ground effect
- Vol. 43, Issue 12, Pages: 52-63(2025)
- 作者机构：
  
  中国航天科工飞航技术研究院磁电总体部,北京,100074
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2024.0082
  CLC： V475.2
- Published：2025
- 稿件说明：
移动端阅览
罗星东, 侯自豪. NACA0012低跨声速近地俯仰迟滞特性研究[J]. 空气动力学学报, 2025, 43(12): 52−63.

LUO Xingdong, HOU Zihao. Research on the hysteresis properties of a pitching NACA0012 airfoil under low transonic ground effect[J]. 2025, 43(12): 52-63.
罗星东, 侯自豪. NACA0012低跨声速近地俯仰迟滞特性研究[J]. 空气动力学学报, 2025, 43(12): 52−63. DOI： 10.7638/kqdlxxb-2024.0082

LUO Xingdong, HOU Zihao. Research on the hysteresis properties of a pitching NACA0012 airfoil under low transonic ground effect[J]. 2025, 43(12): 52-63. DOI： 10.7638/kqdlxxb-2024.0082.

摘要

针对电磁助推近地起飞过程中面临的俯仰振动问题，以NACA0012翼型为研究对象，提出了跨声速静态地面效应的分层依据，对比了各分层中的流动模态及气动特性，随后研究了地面效应、减缩频率对俯仰迟滞特性的影响，并分析了迟滞环形态、转向、饱满度变化的原因。结果表明，翼型下方流道收缩比与等熵极限的差值是对地面效应分层及判断流动模态的重要依据。含攻角影响下的跨声速静态地面效应可分为3个层次，依次是呈整体通流的第1层次、呈通流-壅塞交替的第2层次和呈完全壅塞的第3层次。与之相对应，其近地俯仰迟滞特性也呈现出层次性。在第1层地面效应中，由于效应相对较弱，迟滞特性与自由流相近。在第2层地面效应中，随着效应增强，壅塞效应使得振荡激波S2发生“驻定”或“驻定位置向后缘靠近”，分别导致了迟滞环缩小和整体平移。在第3层地面效应中，由于壅塞溢流加剧，振荡激波S1和S2在正攻角下差异较大，而在负攻角下差异较小，使得迟滞环形态由椭圆状发展为“水滴状”，增大减缩频率能够使迟滞环重新转变为椭圆状。此外，不同层次内的俯仰迟滞特性也呈现出共性特征，如力矩迟滞环都是逆时针转向，升力迟滞环转向与曲线相位的正负变化保持一致；低频俯仰呈现准稳态，而高频俯仰却表现出强迟滞性。

Abstract

Based on an investigation of pitch oscillation encountered during electromagnetic-assisted near-ground takeoff of a NACA0012 airfoil

this study proposes a layering criterion for transonic static ground effects. First

the flow patterns and aerodynamic characteristics within each layer were examined. Subsequently

the influences of ground effects and reduced frequencies on pitch hysteresis properties were analyzed

with emphasis on the mechanisms governing variations in hysteresis loop morphology

steering direction

and fullness. The results indicate that the difference between the flow channel contraction ratio beneath the airfoil and the isentropic limit serves as a critical parameter for characterizing ground effects and determining flow regimes. Under varying angles of attack

transonic static ground effects can be categorized into three distinct layers: Layer 1

with unobstructed flow throughout; Layer 2

exhibiting alternating unobstructed and choked states; and Layer 3

demonstrating fully choked flow. Correspondingly

near-ground pitch hysteresis characteristics show layer-dependent behaviors. In Layer 1

hysteresis properties resemble those in free space due to weak ground effects. In Layer 2

intensified ground effects induce choking

causing the oscillating shock wave S2 to become stationary or shift toward the trailing edge

which results in hysteresis loop contraction or translational displacement

respectively. In Layer 3

severe choking and overflow lead to significant differences between oscillating shock waves S1 and S2 at positive angles of attack but minimal differences at negative angles

transforming hysteresis loops from elliptical to "water droplet" shapes. Increasing the reduced frequency can revert this morphology to elliptical. Common characteristics persist across all layers

including counterclockwise-rotating moment hysteresis loops

lift hysteresis loop steering synchronized with changes in the sign of the curve phase

quasi-steady behavior during low-frequency pitching

and pronounced hysteresis at high frequencies.

关键词

Keywords

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