关键词: 分布式推进, 涵道风扇, 气动/推进耦合, 风洞试验, 飞行器

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