Vehicle-mounted test of propulsion/aerodynamic coupling in a distributed-electric-propulsion tandem-wing layout

A systematic ground-based vehicle-mounted test study is conducted to investigate the propulsion/aerodynamic coupling characteristics of a distributed propulsion tandem-wing configuration aircraft at high angles of attack. Utilizing a self-developed high-precision vehicle-mounted testing platform, aerodynamic performance tests are performed on both a distributed propulsion wing section and a full tandem-wing configuration model under various rotational speeds and angles of attack. This yielded comprehensive data on coupled lift, coupled drag, and pitching moment. The research revealed the significant influence of ducted fan rotational speed on the stall angle of attack, maximum coupled lift, and longitudinal static stability. Notable aerodynamic interference effects between the front and rear wings in the tandem-wing configuration are also identified. Furthermore, a method for adjusting static stability through the differential rotational speeds of the front and rear ducted fans is proposed. This method effectively expanded the stable angle-of-attack envelope of the aircraft, providing crucial experimental evidence and data support for the aerodynamic design and control of distributed propulsion vertical/short take-off and landing aircraft.