带下表面射流的超临界翼型优化  

OPTIMIZATION OF SUPERCRITICAL AIRFOIL WITH JET ON THE LOWER SURFACE OF TRAILING EDGE

作　　者：戴雅雪 应培 王波[1] 马晓平 DAI Ya-xue;YING Pei;WANG Bo;MA Xiao-ping(Institute of Engineering Thermophysics,Chinese Academy of Sciences,Beijing 100190,China;School of Aeronautics and Astronautics,University of Chinese Academy of Sciences,Beijing 100049,China)

机构地区：[1]中国科学院工程热物理研究所,北京100190 [2]中国科学院大学航空宇航学院,北京100049

出　　处：《工程力学》2024年第11期248-256,共9页Engineering Mechanics

基　　金：国家自然科学基金项目(12102431,11902320)。

摘　　要：为探究跨声速工况下超临界翼型RAE2822带下表面射流(jet on the lower surface of trailing edge,LSTE jet)的气动力特性,采用Navier-Stokes(Reynolds Average Navier-Stokes,RANS)控制方程结合Spalart-Allmaras(SA)湍流模型的方法进行数值模拟分析。研究发现,在上翼面存在激波的情况下,下表面射流在增大翼型升力的同时也增大了波阻。提出下表面射流伴随优化进程的射流翼型一体优化思路。采用基于Kriging代理模型的优化方法,以最大化升阻比为目标,对RAE2822翼型分别进行了基准外形优化和带下表面射流(cμ=0.0002)的翼型优化。结果表明:在Ma=0.73、Re=6.5×10^(6)、α=2°的工况下,相较于基准翼型,下表面射流翼型等效升阻比提高了4.9%,下表面射流优化翼型等效升阻比提高了26.2%。带下表面射流翼型的射流翼型一体优化设计方法,能够显著提高超临界翼型的等效升阻比,研究结果有助于下表面射流的应用研究。To investigate the aerodynamic characteristics of a supercritical airfoil RAE2822 with jet on the lower surface of trailing edge(LSTE jet)in transonic conditions,Reynolds Average Navier-Stokes(RANS)equation and Spalart-Allmaras(SA)turbulence model are adopted for the numerical simulation.The results show that the LSTE jet increases the wave drag and the lift of the airfoil when there is a shock wave on the upper wing.The overall optimization method of the airfoil with LSTE jet is proposed.The optimization method based on Kriging surrogate model is adopted to optimize the shape of RAE2822 airfoil without and with LSTE jet(cμ=0.0002)to achieve the maximum lift-to-drag ratio.The results show that compared with the baseline airfoil,the equivalent lift-to-drag ratio of the airfoil with LSTE jet is increased by 4.9%and the equivalent lift-to-drag ratio of the optimized airfoil with LSTE jet is increased by 26.2%when Ma=0.73,Re=6.5×10^(6),α=2°.The overall optimization design method of airfoil with LSTE jet can significantly improve the equivalent lift-to-drag ratio of supercritical airfoil,and the research results are helpful to the application of LSTE jet.

关 键 词：主动流动控制 下表面射流 超临界翼型 气动性能 翼型优化设计 

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]