郑州航空工业管理学院学报

研究将动力系统安置机翼后缘情况下，动力系统所形成的流场对飞机机翼气动特性产生的影响。通过一系列风洞试验，对机翼在动力流场干扰下的气动特性进行测定，即在机翼襟翼放下角度、机翼迎角变化时，对机翼的升力、阻力、俯仰力矩进行测定，进而分析总结后置动力系统对机翼气动特性和增升效果的影响规律。研究结果表明：后置动力系统能够延缓动力前方机翼表面气流分离，稳定机翼表面气流流动；当雷诺数Re=3.24×10⁵且有后置动力系统时，机翼气动性能更为优越；飞机机翼的失速迎角提升至16°时，升力系数增大，最大增长率为6.02%，同时多缝襟翼的气动特性和增升效果普遍提升；当迎角为6°时，升阻比较为稳定，最大提升率为5.73%。

In order to explore the influence of the flow field generated by an aft-mounted propulsion system on the aerodynamic characteristics of aircraft wings, a series of wind tunnel tests are carried out to measure the aerodynamic characteristics of the wing under the interference of the dynamic flow field. Specifically, the lift, drag and pitching moment of the wing are measured under varying flap deflection angles and angles of attack, thereby analyzing the influence patterns of the aft-mounted propulsion system on the aerodynamic characteristics and lift-enhancement effects of the wing. Results show that the use of the aft-mounted propulsion system can delay the separation of airflow on the upper surface of the wing in front of the system and stabilize the surface airflow flow. At a Reynolds number of 3.24×10⁵, the wing exhibits improved aerodynamic performance with the aft-mounted propulsion system: the stall angle of attack increases to 16°, and the lift coefficient rises with a maximum growth rate of 6.02%. The aerodynamic characteristics and lifting effect of the multi-element airfoil are also generally improved. The lift drag ratio is relatively stable when the angle of attack is 6°, with the maximum lift rate of 5.73%.