串列翼布局分布式推进/气动耦合特性车载试验OA

A systematic ground-based vehicle-mounted test study is conducted to investigate the propulsion/aerody-namic 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 per-formed on both a distributed propulsion wing section and a full tandem-wing configuration model under various rota-tional speeds and angles of attack.This yielded comprehensive data on coupled lift,coupled drag,and pitching mo-ment.The research revealed the significant influence of ducted fan rotational speed on the stall angle of attack,maxi-mum 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 aerody-namic design and control of distributed propulsion vertical/short take-off and landing aircraft.