分布式推进飞行器纵向气动/推进耦合效应

doi:10.7527/S1000-6893.2025.32280

Abstract

Abstract:

An aircraft with wing-mounted distributed propulsion has great application potential in lift increase， control， noise reduction， etc. In order to explore the longitudinal aerodynamic coupling effect of the configuration， the longitudinal aerodynamic/propulsion coupling effect of a new type of distributed propulsion aircraft with wing/body fusion and ducted/wing fusion was studied by wind tunnel test and numerical simulation. The wind tunnel test uses a high-precision six-component balance to measure the force of the aircraft， and the numerical simulation uses high-efficiency intake and exhaust boundary method. The aerodynamic force is modified by introducing the concept of fan disk thrust， and the modified aerodynamic force is in good agreement with the wind tunnel test results， which verifies the reliability of the calculation method. The analysis results show that the longitudinal aerodynamic/propulsion coupling effect is closely related to the fan disk thrust coefficient， and the lift， drag and pitching moment coefficients increase， decrease and decrease respectively with the increase of the fan disk thrust coefficient； the lift increase of the ducted fans is proportional to the square root of the thrust coefficient， and the proportional coefficient increases with the increase of angle of attack； the slope of the curve of lift coefficient changing with angle of attack increases slightly with the increase of the fan disk thrust； the fan disk thrust has little influence on the longitudinal static stability of the aircraft.

Key words: distributed propulsion, ducted fans, aerodynamic/propulsion coupling, wind tunnel test, aircraft

CLC Number:

V275

Bei LIU, Xingya DA, Yaowu ZHU, Yuan YI. Longitudinal aerodynamic/propulsion coupling effects of a distributed propulsion aircraft[J]. Acta Aeronautica et Astronautica Sinica, 2026, 47(4): 132280.

Figures/Tables 20

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入口总压/Pa	入口静压/Pa	出口总压/Pa	出口静压/Pa	功率/kW	总推力，风扇盘推力/kg	流量/（kg·s^-1）
93 652	92 702	94 631	93 631	0.42	1.14，0.68	0.42
93 673	91 766	95 601	93 573	1.06	2.25，1.33	0.53
93 656	91 014	96 342	93 501	1.62	3.11，1.84	0.70
93 662	90 553	96 827	93 463	1.97	3.61，2.15	0.77
93 665	89 800	97 601	93 402	2.68	4.57，2.65	0.84
93 658	88 753	98 569	93 311	3.55	5.67，3.26	0.89

计算状态	网格量/10⁴	升力系数/%	阻力系数/%	俯仰力矩系数/%
4°迎角，3.03 kW	1 231
	1 920	1.23	-0.58	-0.98
	2 706	1.40	-0.77	-1.26
计算状态	网格量/10⁴	升力系数/%	阻力系数/%	俯仰力矩系数/%
12°迎角，3.03 kW	1 231
	1 920	1.26	-0.42	-1.16
	2 706	1.48	-0.68	-1.68

Longitudinal aerodynamic/propulsion coupling effects of a distributed propulsion aircraft

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