于彦泽, 刘景飞, 蒋增, 陈宝. 大型飞机后体流动控制及减阻机理研究[J]. 空气动力学学报, 2011, 29(5): 640-644. DOI: 130.25/j.issn.0258-1825.2011.05.017
引用本文: 于彦泽, 刘景飞, 蒋增, 陈宝. 大型飞机后体流动控制及减阻机理研究[J]. 空气动力学学报, 2011, 29(5): 640-644. DOI: 130.25/j.issn.0258-1825.2011.05.017
YU Yan-ze, JIANG Zeng-yan, CHEN bao, . The investigation of flow control and drag reduction mechanism for transport airplane aft-body[J]. ACTA AERODYNAMICA SINICA, 2011, 29(5): 640-644. DOI: 130.25/j.issn.0258-1825.2011.05.017
Citation: YU Yan-ze, JIANG Zeng-yan, CHEN bao, . The investigation of flow control and drag reduction mechanism for transport airplane aft-body[J]. ACTA AERODYNAMICA SINICA, 2011, 29(5): 640-644. DOI: 130.25/j.issn.0258-1825.2011.05.017

大型飞机后体流动控制及减阻机理研究

The investigation of flow control and drag reduction mechanism for transport airplane aft-body

  • 摘要: 通过数值模拟方法研究了大型飞机机身后体的流动特征和机理,并采用涡流发生器对机身后体流动分离进行控制,分析了其控制减阻的机理,讨论了不同参数对减阻效率的影响。计算结果表明:大型飞机机身后体流动分离是导致巡航阻力增加的一个重要因素;在后体底部附近安装涡流发生器,当来流迎角为负时减阻效果较明显,随着迎角的逐渐增大,减阻效果降低;涡流发生器的尺寸、周向距离、安装在机身后体上的前后位置、安装角度等参数对减阻效果具有显著影响。

     

    Abstract: Abstract In this paper, numerical simulation has been used to research the flow characteristics and mechanism of transport aircraft aft-body, vortex generators were used to control separated flows of aft-body, and it got an analysis of drag reduction mechanism by controlled, and also discussed the effect of different parameters on drag reduction. Calculation results show that: the drag of transport airplane aftbody is mainly caused by the flow separation of aft-body; vortex generators were fixed on the bottom of aft-body, and reached a certain drag reduction in the negative angle of attack. Size, circumferential distance and the forward or after location on the body of vortex generator have a certain influence with the drag reduction results.

     

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