Performance analysis and flow mechanism of channel wing considering propeller slipstream

Abstract

The development of the Urban Air Mobility concept has proposed stringent requirements for the fixed-wing vehicle’s Short/Vertical Take-Off and Landing (S/VTOL) performance. With its lift-enhancing impact, the channel wing, can improve aircraft low-speed performance and Short Take-Off and Landing (STOL) capability. It is critical for the performance analysis and flow mechanism study of a channel wing that considers the influence of propeller slipstream to guide the design of S/VTOL aircraft. The law and mechanism for the effect of the enclosing angle of the arc wing, the phase angle of the propeller, the tip clearance, the rotational speed and the chordwise position of the propeller on the channel wing are explored utilizing the quasi-steady multi reference frame method. A channel wing with a larger enclosing angle has a better ability to enhance lift and reduce drag using propeller slipstream. The effect of propeller phase angle on channel wing aerodynamic forces is periodic and weak. Increasing propeller rotational speed is helpful to enhance lift and resist flow separation for channel wing. It can reduce drag for tractor configuration but increase drag for pusher configuration. However, the nose-down pitching moment of a channel wing will grow dramatically, making longitudinal trimming in aircraft layout design challenging.