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中文摘要：
针对太阳能无人机螺旋桨滑流与机翼的气动干扰,考虑了低雷诺数流动下气体黏性和压缩性影响,并根据黎曼边界条件和涡量等效原则建立了能够快速计算分析螺旋桨-机翼气动干扰的非定常面元/黏性涡粒子的混合方法。首先使用有试验数据的风洞模型以及数值模拟技术对混合方法进行验证,在此基础上研究了不同安装位置与工况下螺旋桨与机翼的气动干扰。结果表明：螺旋桨对轴向气流的加速以及滑流诱导的上洗和下洗效应使机翼气动力呈现出增升增阻的现象,机翼升阻比有所下降。较大的弦向间距以及较高的垂直安装位置在减缓机翼升阻比下降的同时也使得螺旋桨拉力有所减小。对于多个螺旋桨的气动干扰,不同的桨叶旋转方向导致机翼气动力不同的变化规律,当旋转方向与机翼翼尖涡反向时,螺旋桨滑流能够抑制翼尖涡的强度,提高机翼气动效率。
英文摘要：
An unsteady panel/viscous vortex particle hybrid method,with the consideration of air viscous and compressibility effects at low Reynold number,is developed base on equivalent vorticity principle and Neumann boundary condition to rapidly calculate the aerodynamic interaction between the wing and the propeller of the solar-powered airplane.Experimental data are compared with computation method to validate the hybrid method proposed.The aerodynamic interactions between the propeller and the wing are investigated at different installation positions and working conditions.Calculated results indicate that the distribution of the spanwise and the chordwise pressure are apparently changed by the increased axial velocity and upwash and downwash effects induced by the propeller slipstream to lead to a decrease of lift-tot-drag ratio.A larger chordwise distance and a higher vertical installation position can reduce propeller thrusts,and can also decelerate lift-to-drag ratio of the wing.For the case of multi propeller interactions,different rotation directions cause different aerodynamic characteristics of the wing.When the propeller rotation direction is opposite to the wing tip vortex direction,the propeller slipstreams can counteract vortex strengths at the wing tip to induce an augment of lift-to-drag ratio of the wing.
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