分布式动力翼气动/推进耦合模型与实验验证

doi:10.7527/S1000-6893.2025.32792

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分布式动力翼气动/推进耦合模型与实验验证

秦嘉琛¹,周洲¹,王睿²,王科雷³

1. 西北工业大学
2. 西北工业大学航空学院
3. 陕西省西安市西北工业大学航空学院

收稿日期:2025-09-17 修回日期:2025-12-29 出版日期:2026-01-09 发布日期:2026-01-09
通讯作者: 周洲
基金资助:
装备预研项目;航空科学基金;装备理论基金

Aerodynamic/propulsive coupling model and experimental validation of distributed propulsion wing

¹,Zhou ZHOUWANG RuiKe-Lei WANG¹

Received:2025-09-17 Revised:2025-12-29 Online:2026-01-09 Published:2026-01-09
Contact: Zhou ZHOU

摘要/Abstract

摘要： 针对分布式动力垂直起降飞行器，提出了相同前进比下气动特性的相似性准则，并将前进比作为描述气动/推进耦合效应的特征参数，建立分布式动力翼随前进比变化的气动力模型，并揭示了前进比对动力翼气动特性的影响规律。然后通过风洞实验和地面车载实验验证了相同前进比下气动特性的相似性准则与所建立模型的实际预测效果。结果表明，气动/推进耦合模型预测结果与实验数据具有较高的一致性，归一化均方根误差不超过10%，能够满足动力学系统与飞行控制系统仿真的精确性与实时性需求，为分布式动力垂直起降飞行器的建模方法提供了理论参考。

关键词: 气动/推进耦合, 分布式动力翼, 涵道单元, 风洞, 车载实验

Abstract: For distributed propulsion vertical take-off and landing (VTOL) aircraft, a similarity criterion of aerodynamic characteristics under identical advance ratios is proposed. The advance ratio is employed as a characteristic parameter to describe the aerodynamic/propulsive coupling effect, and an aerodynamic model of the distributed propulsion wing varying with advance ratio is established. The influence of advance ratio on the aerodynamic characteristics of the propulsion wing is then revealed. Wind tunnel and car-top tests are conducted to verify the similarity criterion of aerodynamic characteristics under identical advance ratios, as well as the predictive performance of the proposed model. Results show that the predictions of the aerodynamic/propulsive coupling model exhibit high consistency with experimental data, with the normalized root mean square error not exceeding 10%. The model thereby satisfies the accuracy and real-time requirements of flight dynamics and flight control systems simulation, providing theoretical support for modeling approaches of distributed propulsion VTOL aircraft.

Key words: aerodynamic/propulsive coupling, distributed propulsion wing, ducted unit, wind tunnels, car-top test

中图分类号:

V211

秦嘉琛周洲王睿王科雷. 分布式动力翼气动/推进耦合模型与实验验证[J]. 航空学报, doi: 10.7527/S1000-6893.2025.32792.

Zhou ZHOU WANG Rui Ke-Lei WANG. Aerodynamic/propulsive coupling model and experimental validation of distributed propulsion wing[J]. Acta Aeronautica et Astronautica Sinica, doi: 10.7527/S1000-6893.2025.32792.

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E-mail：hkxb@buaa.edu.cn

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分布式动力翼气动/推进耦合模型与实验验证

Aerodynamic/propulsive coupling model and experimental validation of distributed propulsion wing

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