摘要
为了验证多参考系模型方法对于螺旋桨气动性能的定常数值模拟仿真的正确性与实用性,以螺旋桨-机翼为研究对象,建立三维模型,基于Navier-Stokes方程和Spalart-Allmaras湍流模型的多参考系模型方法仿真得出螺旋桨不同转速情况下的拉力、扭矩;与测试台相同转速下采集的实验结果进行对比,得出拉力的相对误差平均值在1.77%以内,扭矩的相对误差平均值在27.45%以内,分析螺旋桨不同安装位置对机翼气动性能的影响。结果表明:实验结果与基于多参考系模型的数值模拟方法结果有较好的一致性,机翼的升力系数与阻力系数在前置螺旋桨滑流的影响下同时增加,总的升阻比下降;螺旋桨的转动在其转轴两侧产生了上洗和下洗效应,机翼的当地迎角相应增大和减小。
In order to verify the correctness and practicability of the multi-reference system model method for the constant numerical simulation of propeller aerodynamic performance,a 3D model was established with propeller-wing as the research object.Based on the Navier-Stokes equation and Spalart-Allmaras turbulence model,the multi-reference system model method was used to simulate the pulling force and torque of the propeller at different speeds.Compared with the experimental results collected at the same speed of the test bench for verification and analysis,the relative error average value of the pulling force was within 1.77%,the relative error average value of torque was within 27.45%,and the influence of different installation positions of the propeller on the aerodynamic performance of the wing was analyzed.The results show that the experimental results are in good agreement with the results of the numerical simulation method based on the multi-reference system model.The lift coefficient and drag coefficient of the wing increase simultaneously under the influence of the slipstream of the front propeller,and the total lift-to-drag ratio decreases.The rotation of the propeller creates an upwash and downwash effect on either side of its rotation axis,the local attack angle of the wing increases and decreases accordingly.
作者
吴浩
石永康
赵越
邹楠
郭稳敏
WU Hao;SHI Yongkang;ZHAO Yue;ZOU Nan;GUO Wenmin(Intelligent Manufacturing Modern Industry College,Xinjiang University,Urumqi Xinjiang 830000,China)
出处
《机床与液压》
北大核心
2024年第14期1-6,共6页
Machine Tool & Hydraulics
基金
国家自然科学基金地区科学基金项目(51965056)
自治区高层次人才项目(100400027)
自治区高校科研计划项目(61021800081)
新疆大学科研启动项目(620312351)。
关键词
螺旋桨
数值模拟
多参考系模型
气动性能
propeller
numerical simulation
multi-reference frame model
aerodynamic performance
作者简介
吴浩(1998-),男,硕士研究生,研究方向为无人机结构设计。E-mail:2670685781@qq.com;通信作者:石永康(1983-),男,博士,副教授,主要研究方向为无人机飞控算法。E-mail:shiyongkang2021@163.com。
