高亚声速低雷诺数翼型气动优化设计研究  

Optimal aerodynamic design of low Reynolds number airfoil under high subsonic condition

作　　者：李帝辰 杨龙 魏闯[1] 张铁军[1] LI Dichen;YANG Long;WEI Chuang;ZHANG Tiejun(Aero Science Key Laboratory of High Reynolds Aerodynamic Force at High Speed,AVIC Aerodynamics Research Institute,Shenyang 110034,China)

机构地区：[1]中国航空工业空气动力研究院高速高雷诺数气动力航空科技重点实验室,辽宁沈阳110034

出　　处：《飞行力学》2022年第5期14-21,共8页Flight Dynamics

摘　　要：针对临近空间和火星飞行器的螺旋桨通常面临的高亚声速、低雷诺数的特殊气动问题,首先,结合经过验证的基于■转捩模型的RANS数值模拟方法,并基于代理模型建立了高亚声速、低雷诺数气动优化设计框架。然后,针对临近空间螺旋桨翼型,在设计工况点(Ma=0.77,Re=1×10^(5))开展了以改善升阻比为目标的气动优化设计。结果表明,优化翼型较原始低速翼型升阻比在设计点附近大幅提升,气动性能得到显著提高。研究结果可为临近空间和火星飞行器的气动设计提供技术支持。The high subsonic and low Reynolds number regime poses severe challenges to propellers of near space vehicle and Mars exploration aircraft.Aiming at this rarely studied aerodynamic problem,based on surrogate model optimization design method,and a validated steady RANS solver coupled with ■ transition model,this paper conducted an aerodynamic optimization design study,to improve the lift-to-drag ratio of high subsonic and low Reynolds number propeller airfoil at design condition(Ma=0.77,Re=1×10^(5)).The results indicate that the lift-to-drag ratio of the optimal airfoil is remarkably increased.The study can provide technical support to the design of near space vehicle and Mars exploration aircraft.

关 键 词：低雷诺数 跨声速流动 代理模型优化 临近空间 

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] V411