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.
作者
李帝辰
杨龙
魏闯
张铁军
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)
出处
《飞行力学》
CSCD
北大核心
2022年第5期14-21,共8页
Flight Dynamics
关键词
低雷诺数
跨声速流动
代理模型优化
临近空间
low Reynolds number
transonic flow
surrogate model optimization
near space
