基于气动载荷分布的螺旋桨诱导流场重构设计

Based on the innovative developing concept of the distributed electric propulsion aircrafts, the reconstruction design of the propeller induced flow-filed is carried out in this study to obtain the maximum propeller/wing integrated aerodynamic efficiency. First, the quasi-steady numerical simulation technique is developed based on the momentum source method, then the relationship between the aerodynamic loading distributions and the propeller induced flow-field properties is established. Second, the optimization design method developed for the reconstruction of the propeller induced flow-field is proposed by controlling the parameterized aerodynamic loading distribution profiles. Finally, both the reliability and efficiency of the proposed aerodynamic design concept are studied. The results show that compared with the minimum induced loss propeller, the optimized aerodynamic loading distributions on the propeller disk lead to significant improvement of the wing aerodynamic performance under the slipstream effect. As a result, the wing section has a relative lift augmentation of 10.40%, a relative drag decrease of 7.05%, and a relative lift-to-drag increment of 18.77%.