分布式涵道风扇-机翼耦合构型因其复杂的部件和气动耦合效应，准确且高效地求解其气动特性是一项挑战性任务。为此，本文提出了一种基于雷诺平均纳维-斯托克斯（RANS）方程并充分考虑多部件气动-推进耦合效应的分布式涵道风扇动量源方法。该方法通过简化风扇动静叶的流场计算，大幅提高计算效率，同时准确捕捉机翼边界层粘性效应、涵道唇口加速效应及排气道尾迹等部件耦合影响，从而准确预测机翼、涵道唇口和排气道等部件的气动性能。具体而言，该方法首先使用 RANS 方程结合多重参考坐标系（MRF）方法计算准定常流场，提取交界面处的三方向速度、湍动能和涡耗散率等信息，并将其作为边界条件施加于无风扇构型，以模拟涵道风扇的动力效应。在单涵道风扇-翼段耦合构型测试中，该方法在单一构型下提取的流场信息可准确预测较大迎角范围内的同构型气动性能及不同翼型构型下的气动性能。与 MRF 方法相比，在2°~16°迎角下，本文方法计算的升力系数相对误差小于 2%，阻力系数相对误差小于 4.5%，并减少计算耗时超过90%，计算精度优于传统动量源方法。在分布式涵道风扇-机翼耦合构型测试中，该方法同样表现出较高精度与显著的效率优势，为分布式涵道风扇构型的气动性能预测提供了一种高效、可靠的工具。
Due to its complex component composition and aerodynamic coupling effect, it is a challenging task to accurately and efficiently predict the aerodynamic characteristics of the distributed ducted fan-wing coupling configuration. To this end, this paper proposes a distributed ducted fan momentum source method based on the Reynolds-averaged Navier-Stokes (RANS) equations and fully considering the aerodynamic-propulsion coupling effect of multiple com-ponents. This method greatly improves the computational efficiency by simplifying the flow field calculation of the rotor and stator blades, while accurately capturing the wing boundary layer viscosity effect, the duct lip acceleration effect, and the exhaust duct wake effect, thereby accurately predicting the aerodynamic performance of components such as the wing, duct lip, and exhaust duct. Specifically, this method uses the RANS equation combined with the multiple reference frame (MRF) method to calculate the quasi-steady flow field, extracts information such as the three-directional velocity, turbulent kinetic energy, and eddy dissipation rate at the interface, and applies it as a boundary condition to the fan-less configuration to simulate the dynamic effect of the ducted fan. In the single ducted fan-wing section coupled configuration test, compared with the MRF method, the lift coefficient calculated by this method has a relative error of less than 2%, and the drag coefficient has a relative error of less than 4.5%, and the calculation time is reduced by more than 90%, and the calculation accuracy is better than the traditional momentum source method. In addition, the study shows that the flow field information extracted by this method under a single configuration can accurately predict the aerodynamic performance of the same configuration within a large angle of attack range and the aerodynamic performance under different airfoil configurations. In the distributed ducted fan-wing coupled configuration test, this method also shows high accuracy and significant efficiency advantages, providing a reliable and efficient tool for predicting the aerodynamic performance of distributed ducted fan configu-rations.
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