基于高精度格式的翼型失速特性脱体涡数值模拟  

Detached Eddy Simulation of the Airfoil Stall Characteristics Using High Order Numerical Scheme

作　　者：王瑞 钟伯文 WANG Rui;ZHONG Bowen

机构地区：[1]南昌航空大学飞行器工程学院,南昌330063 [2]江西省飞行器设计与气动仿真重点实验室,南昌330063

出　　处：《科技创新与应用》2023年第24期29-33,共5页Technology Innovation and Application

基　　金：国家自然科学基金(12262023)。

摘　　要：该文采用脱体涡模拟方法(DES),引入低耗散近似黎曼解HLLC格式并结合五阶WENO高精度数值格式对NACA0015后缘失速翼型在大攻角及失速状态下的流场进行数值模拟。通过与风洞实验结果进行对比,讨论高阶精度数值格式对DES方法失速气动特性的预测效果。结果表明,HLLC+五阶WENO格式与二阶Jameson中心差分格式相比能够提高DES方法翼型失速特性的预测精度,HLLC+五阶WENO格式精度高、耗散性较低,能够捕捉更小尺度的湍流涡结构。Detached Eddy Simulation(DES)is conducted to simulate the flow field around the NACA0015 airfoil at large angle of attack and stall state by introducing the low dissipation approximate Riemann solver HLLC combined with the fifth-order WENO numerical scheme.Simulation results are compared with wind tunnel test results,and the influence of high order numerical scheme on stall aerodynamic characteristic prediction by DES method is discussed.The results show that compared with the second order Jameson central difference scheme,the high order HLLC+WENO scheme can improve the prediction accuracy of the stall characteristics of the airfoil.The high-order HLLC+WENO scheme has lower dissipation and can capture smaller scales of the turbulent eddy structures than CDS.

关 键 词：HLLC+五阶WENO格式 Jameson中心差分格式 脱体涡模拟 翼型失速特性预测 数值模拟 

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]