共轴刚性旋翼悬停及高速前飞状态气动干扰特性研究  

Study on Aerodynamic Interference Characteristics of Coaxial Rigid Rotor Hovering and High-Speed Forward Flight

作　　者：肖升兴 张超 张华[1] 崔钊 XIAO Shengxing;ZHANG Chao;ZHANG Hua;CUI Zhao

机构地区：[1]中国飞行试验研究院,陕西西安710089

出　　处：《科技创新与应用》2020年第10期1-4,8,共5页Technology Innovation and Application

摘　　要：文章建立了一种基于N-S方程的共轴刚性旋翼流场数值模拟方法。通过对比不同前行桨尖马赫数旋翼的实验结果,验证了该方法的准确性和模拟ABC旋翼的适用性。运用商业软件ANSYS ICEM划分非结构化网格,采用了滑移网格和动网格技术,在FLUENT求解器中使用UDF程序实现了桨叶周期变距运动,对在悬停及大速度前飞状态下的XH-59A旋翼流场进行了数值模拟计算。计算结果表明:XH-59A旋翼在悬停状态上旋翼对下旋翼的气动干扰比较大,但随着前飞速度的增加,干扰逐渐减小;上下旋翼间的气动干扰随总距的增加呈先增大后减小的趋势。A numerical simulation method of coaxial rigid rotor flow field based on NS equation is established.The accuracy of the method and the applicability of the simulated ABC rotor are verified by comparing the experimental results of the different forward propeller.Using the commercial software ANSYS ICEM to divide the unstructured grid,using the sliding mesh and dynamic mesh technology,the FLUENT solver uses the UDF program to achieve the blade periodic variable motion,before the hover and the high velocity.The aerodynamic characteristics of the XH-59A rotor were analyzed.The simulation of the flow field of the rigid rotor XH-59A shows that the aerodynamic characteristics are in agreement with the experimental results.The aerodynamic interference of the upper rotor to the lower rotor in the hovering state is relatively large,but the interference decreases with the increase of the forward speed.

关 键 词：共轴刚性旋翼 气动干扰 XH-59A 滑移/动网格 高速前飞 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]