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为研究带有边界层抽吸的分布式动力系统尾缘射流对机身气动性能及推进效率的影响,将机身简化为二维翼型,并加入尾缘射流及边界层抽吸的作用,利用数值模拟的手段来研究来流攻角、射流偏转角、边界层抽吸对推进效率及气动性能的影响,为分布式动力系统的设计与应用提供初步的建议.结果表明在中、小来流攻角(2°及0.6°)的情况下尾缘射流及边界层抽吸能够提高升阻比,推进效率可超过80%;而在大来流攻角(4°)情况下射流偏转角增大使翼型的阻力大幅上升,对气动性能和推进效率产生极为不利的影响.
In order to study the influence of jet of distributed power system with boundary layer on the aerodynamic performance and propulsion efficiency of the fuselage, the fuselage is simplified to two-dimensional airfoil, and added to the jet and the boundary layer suction, Numerical simulations are used to study the effect of the angle of attack on the flow, the jet deflection angle and the suction on the boundary layer on the propulsive efficiency and aerodynamic performance, and provide preliminary suggestions for the design and application of distributed dynamical systems. At the attack angles of 2 ° and 0.6 °, the trailing edge jet and the boundary layer pumping can increase the lift-drag ratio, and the propulsive efficiency can exceed 80%. In the case of a large angle of attack (4 °), the jet deflection angle Increasing the resistance of the airfoil increases dramatically, which has an extremely adverse effect on aerodynamic performance and propulsion efficiency.