充气式翼型绕流大涡模拟分析  

Research on the Flow Around Inflatable Bump Airfoil with Large Eddy Simulation

作　　者：康小伟[1] 韩维[1] 王允良[1] 郭卫刚[1] 

机构地区：[1]海军航空工程学院飞行器工程系,山东烟台264001

出　　处：《海军航空工程学院学报》2013年第2期137-140,共4页Journal of Naval Aeronautical and Astronautical University

摘　　要：针对多梁式充气机翼的翼型,采用大涡模拟方法对其表面的复杂流动进行了数值仿真研究,得到了其迎角在0°～20°时的流动情况和气动力特性,并与其他仿真结果和风洞试验结果进行了比较分析。结果表明:采用大涡模拟方法得到的计算结果与风洞试验结果较为吻合,可以更好地模拟充气式翼型的表面流动情况。The flow of inflatable bump airfoil was simulated with large eddy simulation, and the aerodynamic per-formance was computed in the range of angles of attack of 0°-20°. Compared to wind tunnel experiments, the analysis for the simulation had been made to investigate the precision with other numerical simulations. It＇s found that large eddy simulation could simulate the flow of inflatable bump airfoil better than other numerical simulation methods.

关 键 词：充气式翼型 数值模拟 大涡模拟 气动特性 

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]