大型水陆两栖飞机吹气襟翼设计与分析验证  

Design and test of a jet flap for a large amphibian

作　　者：孙卫平[1] 杨康智 秦何军[1] 

机构地区：[1]中国航空工业集团公司中航通飞研究院有限公司总体气动研究室,广东珠海519040

出　　处：《航空动力学报》2016年第4期903-909,共7页Journal of Aerospace Power

摘　　要：针对大型水陆两栖飞机的使用特点和指标要求,以原型机翼为基础,重点开展机翼附面层控制增升装置设计技术研究,设计了附面层控制的吹气襟翼方案.采用计算流体动力学方法作为初步设计的评估手段,全面分析评估了设计方案的气动力特性和流场结构,最后通过风洞试验验证了该方案的增升效果.结果显示该设计方案在较宽的吹气动量系数范围内,最大升力系数均有不同程度的增幅,在吹气动量系数约为0.2左右时,获得最大的升力系数增量约为1.0,按照原型机的滑流影响规律推算,当采用吹气襟翼的主动流动控制方案后,起降速度能下降约30%,达到了设计指标.According to the requirements of a large amphibian＇s operating features and performance based on the original wing, a high-lift device design technology of boundary layer control jet flap was studied. The scheme of boundary layer control jet flap was de- signed. By using computational fluid dynamics numerical simulation as a means to assess the preliminary design, the design scheme＇s aerodynamic characteristics and flow field structure were analysed and evaluated, and finally wind tunnel tests were conducted to verify the lift effect of the scheme. The result of the design scheme showed that in a wide range of blowing momentum coefficient, the maximum lift coefficient had varying degrees of growth; when the blowing momentum coefficient was 0.2, the incremental maximum lift coefficient was 1.0; according to the influence of the prototype slipstream projections, when the boundary layer control jet flap was employed, the take off and landing speed could drop about 30%, a- chieving the design target.

关 键 词：水陆两栖飞机 增升装置 吹气襟翼 风洞试验 最大升力系数 起降速度 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]