【摘要】 针对串列翼飞行器螺旋桨滑流引发气动特性非线性变化的问题，提出基于多重参考系(MRF)模型的滑流效应高精度数值模拟方法。构建旋转坐标系下的雷诺平均纳维-斯托克斯(RANS)方程求解体系，采用压力基稳态求解器与标准壁面函数，通过离心力/科氏力等效旋转效应，实现滑流与机翼干扰的稳态耦合分析。动力测试台验证拉力仿真误差小于等于2%，扭矩误差小于等于8%。在4°攻角工况下，滑流使全机升力系数较无滑流状态提升31.6%，且前翼阻力在正攻角区显著增大(较后翼高48%);桨间距为1.5倍螺旋桨直径时涡干涉最小，拉力系数提升9.2%。结果表明:MRF模型可高精度预测滑流-气动耦合效应;滑流对前翼的气动调控呈强非线性，攻角增大导致升力增益衰减; 1.5倍螺旋桨直径为抑制涡干涉的最佳安装间距。更多还原

【Abstract】 This research develops a high-fidelity numerical simulation method employing the multiple reference frame( MRF) model to resolve propeller slipstream-induced nonlinear aerodynamic variations on a tandem-wing aircraft during cruise. The solution framework solves Reynolds averaged Navier-Stokes( RANS) equations within rotating coordinates. We integrate a pressure-based steady solver with standard wall functions and model rotational effects through centrifugal and Coriolis forces. This approach enable coupled steady-state analysis of slipstream-wing interactions. Dynamometer validation demonstrates thrust simulation errors ≤ 2% and torque errors ≤ 8%. At 4° angle of attack,slipstream increased the total lift coefficient 31. 6% compared to slipstreamoff conditions,while significantly augmenting drag on the forward wing within positive incidence regions-this drag exceeds aft wing drag by 48%. Furthermore,a propeller spacing of 1. 5 D_L( D_L= propeller diameter) minimizes vortex interference and increases thrust coefficient 9. 2%. Results demonstrate that the MRF method predicts slipstream-aerodynamic coupling effects with high accuracy. Slipstream exerts strongly nonlinear aerodynamic influence on the forward wing,with increasing angle of attack attenuating slipstream-induced lift enhancement. The spacing configuration of 1.5D_L offers the optimum distance for suppressing vortex interference.更多还原