飞行器船尾设计对亚声速底阻影响及风洞试验验证  

Analysis and Wind Tunnel Test on the Influence of Boattail Design on Aircraft Base Drag

作　　者：徐国武[1] 罗雨 陈冰雁[1] 关发明[1] 罗小云[1] 岑梦希 XU Guowu;LUO Yu;CHEN Bingyan;GUAN Faming;LUO Xiaoyun;CEN Mengxi(China Academy of Aerospace Aerodynamics,Beijing 100074,China)

机构地区：[1]中国航天空气动力技术研究院,北京100074

出　　处：《力学季刊》2021年第1期149-155,共7页Chinese Quarterly of Mechanics

摘　　要：减小阻力尤其是底部阻力,是飞行器增加航程的重要手段,而船尾布局则是减小底部阻力的有效措施。为研究船尾修型设计在亚声速段对飞行器阻力的影响规律,对某飞行器外形开展船尾修型设计并进行数值模拟,分析了不同船尾形状和船尾角度对飞行器阻力的影响情况,并开展了风洞试验验证。结果表明,船尾修型设计可以有效减小底部阻力;船尾采用曲线过渡的减阻效果优于直线过渡;在限定船尾过渡段尺寸(轴向长度80 mm、法向高度40 mm)的情况下,船尾角度超过45°的修型设计,对底部的减阻效果更为明显;风洞试验结论与数值分析结果一致。Reducing the drag,especially the base drag,is the main means for aircraft to increase its range.And boattail configuration is an effective measure to reduce base drag.In order to investigate the influence of boattail configuration on the aircraft drag in subsonic flow,the design and modification of an aircraft boattail shape were carried out,and the aerodynamic characteristic was numerically simulated.The effects of different boattail shape and boattail angle on aircraft drag were analyzed,and the wind tunnel test was carried out for validation.The results indicate that boattail configuration can effectively reduce the base drag,and the drag reduction effect is better for the curve transition than for the straight transition.As the size of boattail transition section(80 mm in length and 40 mm in height)is limited,the modification design with boattail angle over 45 degrees has more obvious drag reduction effect on the base.The results of wind tunnel test are consistent with those of numerical analysis.

关 键 词：船尾 飞行器阻力 底阻 数值模拟 风洞试验 

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]