小展弦比飞翼大迎角航向稳定性突变与改善措施

赵帅; 金玲; 刘李涛; 郭林亮; 蒋永

doi:10.7527/S1000-6893.2026.33235

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DOI: https://doi.org/10.7527/S1000-6893.2026.33235

小展弦比飞翼大迎角航向稳定性突变与改善措施

赵帅 ,
金玲 ,
刘李涛 ,
郭林亮 ,
蒋永

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1. 中国空气动力研究与发展中低速空气动力研究所
2. 中国空气动力研究与发展中心

收稿日期: 2025-12-15

修回日期: 2026-04-01

网络出版日期: 2026-04-02

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Investigation and improvement on abrupt change of directional stability at high angles of attack for a low-aspect-ratio flying-wing

ZHAO Shuai ,
JIN Ling ,
LIU Li-Tao ,
GUO Lin-Liang ,
JIANG Yong

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Received date: 2025-12-15

Revised date: 2026-04-01

Online published: 2026-04-02

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摘要

小展弦比飞翼布局是未来飞行器的重要发展方向。为进一步摸清此类布局的大迎角气动特性，综合风洞测力试验、流谱试验及数值模拟方法，深入剖析了小展弦比飞翼标模在大迎角工况下的横航向气动力及力矩变化情况。结果表明，来流存在侧滑时，模型横航向气动特性随迎角增加而剧烈变化。迎角超过24°后，全机航向静稳定度急剧下降，并在40°迎角附近达到极值；迎角继续增加至50°时，航向静稳定度又恢复至中小迎角下的水平。分析流场发现，来流侧滑使得模型迎风侧前缘涡破裂提前，背风侧前缘涡破裂推迟，由此导致机头两侧低压区呈现明显的非对称分布，进而诱发强烈的不稳定横向力及偏航力矩。通过将座舱位置后移5%的机身长度，可以降低侧滑引起的非对称低压区在机头高度方向上的投影，削弱机头区域横向力，有效改善大迎角航向稳定性突变问题。

关键词： 小展弦比飞翼; 大迎角; 侧滑; 风洞试验; 数值模拟; 航向稳定性

本文引用格式

赵帅 , 金玲 , 刘李涛 , 郭林亮 , 蒋永 . 小展弦比飞翼大迎角航向稳定性突变与改善措施[J]. 航空学报, 0 : 1 -0 . DOI: 10.7527/S1000-6893.2026.33235

Abstract

The low-aspect-ratio flying-wing configuration is a crucial development direction for future aircraft. To further illustrate the aerodynamic characteristics of such configurations at high angles of attack, a comprehensive analysis of the lat-eral and directional aerodynamic forces and moments of a low-aspect-ratio flying-wing model at high angles of attack was conducted by integrating wind tunnel force measurement tests, flow visualization tests, and numerical simulations. The results indicate that the lateral and directional aerodynamic characteristics of the model change drastically with increasing angle of attack under sideslip conditions. The directional static stability of the aircraft sharply decreases when the angle of attack exceeds 24°, and reaches an extreme value near 40° angle of attack. Moreover, as the angle of attack increases to 50°, the directional static stability returns to the level observed at low and moderate angles of attack. Flow field analysis reveals that sideslip accelerates the leading-edge vortex breakdown on the windward side while delaying the vortex breakdown on the leeward side. This results in a significantly asymmetric distribution of the low-pressure area on the nose, thereby producing strong destabilizing lateral force and yawing moment. Moving the cockpit rearward can reduce the vertical projection of the sideslip-induced asymmetric low-pressure area on the nose. This weakens the destabilizing lateral force in the nose region and can effectively mitigates the abrupt degradation of directional stability at high angles of attack.

Key words： low-aspect-ratio flying-wing; high angle of attack; sideslip; wind tunnel test; numerical simulation; directional static stability

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