Numerical analysis of pressure distribution in a low aspect ratio wing with distributed electric propulsion

The distributed electric propulsion concept expands the boundaries of aircraft designs, therefore, the study of aerodynamic effects on the propulsion/wing interaction is of great importance. This paper focuses on analyzing the pressure distribution in a low aspect ratio wing with distributed electric propulsion concept, considering the propulsion upstream of the wing. Using computational fluid dynamics, the wing pressure was numerically analyzed for different combinations of propeller rotation direction. Numerical methods were based on RANS equations, including the turbulence model, and actuator disk model based on "blade element theory," which was used to represent the propeller. Numerical validation presented good representation of the pressure distributions obtained by the numerical method when compared with experimental data, especially in wing regions affected by the induced flow through the actuator disk. Numerical analysis has shown significant interplay between propeller rotation direction and pressure distribution on the wing, which in turn can influence stall initiation regions due to blade-induced flow.