高效层流翼型设计及试验验证  

Efficient design and experimental verification of laminar airfoil

作　　者：耿延升 艾梦琪 王伟 耿建中 赵彦 GENG Yansheng;AI Mengqi;WANG Wei;GENG Jianzhong;ZHAO Yan(AVIC The First Aircraft Institute,Xi'an 710089,China;Northwestern Polytechnical University,Xi'an 710072,China)

机构地区：[1]航空工业第一飞机设计研究院,西安710089 [2]西北工业大学,西安710072

出　　处：《航空学报》2022年第11期104-114,共11页Acta Aeronautica et Astronautica Sinica

摘　　要：层流机翼设计技术是民用飞机减阻设计重要的发展方向之一。采用CST参数化方法及现代优化算法开展了面向工程应用的层流翼型设计方法研究,基于某层流技术验证机需求设计了一款层流翼型,采用数值计算和高速风洞试验对其层流特性进行了验证研究。研究结果表明,发展的设计方法可以实现层流翼型优化设计及反设计,优化翼型表面的层流区域显著扩大,升阻比有所提升;为验证机设计的层流翼段在设计点具有超过50%的层流区域,较传统翼段减阻量超过10%。研究结果对军民用高亚声速运输类飞机的层流减阻设计具有一定的参考价值。Laminar flow wing design technology is one of the important development directions of civil aircraft drag reduction design. A laminar airfoil design method for engineering applications is studied by using CST parameterization method and modern optimization algorithm. A laminar airfoil is designed based on the requirements of a laminar flow validator, and its laminar flow characteristics are verified by numerical calculation and high-speed wind tunnel test. The results show that the developed design method can realize the optimization design and reverse design of laminar airfoil, the laminar flow area on the optimized airfoil surface is significantly expanded and the lift-drag ratio is improved. The laminar flow section designed for the validator has more than 50% laminar flow area at the design point, and the drag reduction is more than 10% compared with the traditional wing section. The research results have certain reference value for laminar drag reduction design of civil and military high subsonic transport aircraft.

关 键 词：层流机翼 翼型优化 风洞试验 升阻比 转捩 

分 类 号：V211.4[航空宇航科学与技术—航空宇航推进理论与工程]