Aerodynamic Characteristics of Distributed Propulsion/Wing Panel Coupling in Zero-Freestream State

With the rapid development of the aviation industry, enhancing aircraft performance and reducing environmental impact have become key research focuses. This paper analyzes the flow mechanisms of distributed propulsion wings coupled with a rear-mounted flow-inducing wing under zero-freestream (hovering) conditions, as well as the impact of mutual interactions between propulsion units on the aerodynamic and propulsion characteristics. The influence of the deflected flap angle on the coupled unit’s aerodynamic and propulsion characteristics is investigated. As the deflection angle increases, both lift and drag increase. Simultaneously, the ducted jet flow demonstrates significant capability in delaying flow stall. The effect of the deflected flap angle on the lift of the propulsion wing exhibits a complex relationship: the lift initially decreases, then increases, and subsequently decreases again with increasing deflection angle. This variation is attributed to the Venturi effect caused by the compression of the upper and lower jet flows by the deflected flap and its separated flow surface. Increasing the deflected flap chord length elevates both lift and drag, while increased Reynolds number suppresses flow separation. However, the lift increment gradually diminishes with chord length extension, demonstrating marginal effects. Regarding the overall aerodynamic characteristics of distributed propulsion/wing panel (DPWP) coupling model, flow field analysis reveals that under the coupling effect of ducted jet flow, combined upwash and downwash effects cause progressive lift reduction along the spanwise direction. Through the coupled influence of snatching effect and suction effect, thrust progressively increases spanwise.