火星超低雷诺数下螺旋桨气动性能研究  

Aerodynamic Performance of Propeller under Ultra-Low Reynolds Number on Mars

作　　者：张旺旺 徐彬[1,2] 张海涛 樊伟 赵之然 ZHANG Wangwang;XU Bin;ZHANG Haitao;FAN Wei;ZHAO Zhiran(School of Mechanical Engineering,Beijing Institute of Technology,Beijing 100083,China;Chongqing Innovation Center,Beijing Institute of Technology,Chongqing 401120,China)

机构地区：[1]北京理工大学机械与车辆学院,北京100083 [2]北京理工大学重庆创新中心,重庆401120

出　　处：《北京理工大学学报》2024年第2期172-181,共10页Transactions of Beijing Institute of Technology

基　　金：国家自然科学基金资助项目(52102432);重庆市自然科学基金资助项目(CSTB2022NSCQ-MSX1101,CSTC2021JCYJ-MSXMX0792);北京理工大学研究生科研水平和创新能力提升专项计划资助项目(2023YCXY020)。

摘　　要：火星超低雷诺数环境导致螺旋桨系统气动特性相比于地球环境显著恶化,翼型表面层流分离现象影响了火星螺旋桨的气动特性.为设计出适应火星低雷诺数环境的螺旋桨,深入了解超低雷诺数对翼型气动特性的作用机理,采用Transition SST转捩模型求解非定常可压缩N-S方程的数值模拟技术,对几种适用于低雷诺数环境的翼型进行火星超低雷诺数环境下气动特性模拟计算,从而选取最适应火星大气环境的翼型.结果表明CLF5605翼型具有更好的气动性能.对选定的翼型进行不同超低雷诺数下气动特性模拟计算,揭示了超低雷诺数对翼型气动特性的影响,即在火星大气雷诺数范围内,更高的雷诺数对应更好的气动性能;对雷诺数从100~20000翼型表面边界层状态进行数值模拟,发现翼型层流分离结构发生显著变化,从低雷诺数下的层流边界层状态,随着雷诺数的增加开始发生层流分离,在翼型尾缘产生层流分离泡,并最终变成湍流边界层.采用最小能量损失的方法设计火星螺旋桨,对其气动性能进行了数值模拟仿真,并对轻量化制造的螺旋桨进行了地面台架实验验证,通过将地面实验结果与CFD数值模拟仿真结果对比,验证了螺旋桨轻量化设计合理性以及数值计算的准确性.The ultra-low Reynolds number environment of Mars has led to a significant deterioration of the aero-dynamic characteristics of the propeller system compared with the Earth environment,and the laminar flow sep-aration phenomenon on the surface of the airfoil affects the aerodynamic characteristics of the Martian propeller.In order to design a propeller suitable for the low Reynolds number environment of Mars,and to deeply study the mechanism effect of ultra-low Reynolds number on the aerodynamic characteristics of airfoils,a numerical simu-lation method for unsteady compressible N-S equation was proposed based on a Transition SST transfer model,and the aerodynamic characteristics of several airfoils suitable for low Reynolds number environment of Mars were simulated and calculated to select the most suitable airfoil for the Martian atmospheric environment.The results show that the CLF5605 airfoil possesses a better aerodynamic performance.And the aerodynamic charac-teristics of the selected airfoils were simulated and calculated under different ultra-low Reynolds number to re-veal the influence of ultra-low Reynolds number on the aerodynamic characteristics of airfoil,including the range of Reynolds number in the Martian atmosphere and the higher Reynolds number correspond to better aero-dynamic performance.And then,the surface boundary layer state of the airfoil was simulated from 100 to 20000 Reynolds number.The results show the significant changes of the laminar flow separation structure of the airfoil,the laminar flow boundary layer state begins to bring laminar flow separation with the increase of Reynolds num-ber,and some laminar flow separation bubbles are generated at the tail edge of the airfoil,becoming turbulent boundary layer.Finally,according to the method of minimum energy loss,a Mars propeller was designed,simu-lating numerically its aerodynamic performance,carrying out a serious of ground bench experiments to verify for the lightweight propeller,and comparing the ground experimental results with t

关 键 词：超低雷诺数 气动特性 边界层状态 层流分离 轻量化设计 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]