分布式动力翼气动/推进耦合模型与试验验证

doi:10.7527/S1000-6893.2025.32792

Abstract

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 tunnel test, car-top test

CLC Number:

V211

Jiachen QIN, Zhou ZHOU, Rui WANG, Kelei WANG. Aerodynamic/propulsive coupling model and test validation of distributed propulsion wing[J]. Acta Aeronautica et Astronautica Sinica, 2026, 47(12): 132792.

Figures/Tables 16

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前进比J	来流速度 V_∞/（m·s^-1）	油门δ_t	转速n/（r·min^-1）
0.4	10	0.4	5 727
0.4	20	0.9	11 265
0.5	10	0.3	4 672
0.5	20	0.7	9 285
0.7	20	0.45	6 558
0.7	30	0.8	10 454

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

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