民用飞机ADHF构型扰流板下偏气动特性研究  

Research on Aerodynamic Characteristics of AHDF Civil Aviation Aircraft

作　　者：刘苍松 刘沛清[2] 毛俊[1] 李亚林[1] 陈迎春[1] LIU Cang-song;LIU Pei-qing;MAO Jun;LI Ya-lin;CHEN Ying-chun(Shanghai Aircraft Design and Research Institute,Shanghai 201000,China;Beihang University,Beijing 100000,China)

机构地区：[1]上海飞机设计研究院,上海201000 [2]北京航空航天大学,北京100000

出　　处：《航空计算技术》2021年第5期84-86,91,共4页Aeronautical Computing Technique

基　　金：国家自然科学基金项目资助(12002389,12072014)。

摘　　要：采用计算流体力学方法,针对伴随扰流板下偏铰链襟翼构型典型二维多段翼进行数值模拟,研究了扰流板下偏对多段翼气动特性的影响。结果表明:1)缝道参数一致的情况下,扰流板下偏可明显提升增升构型升力;2)随迎角增大,襟翼下偏与扰流板下偏对升力的提升量均存在衰减,但扰流板下偏衰减更为明显,20°迎角下扰流板偏转构型升力增量约为0°迎角的15%,但20°迎角下襟翼偏转构型升力增量约为0°迎角的40%。Using computational fluid dynamics method,numerical simulation is carried out on the typical two dimensional multi segment wing with the deflection hinged flap configuration of spoiler,and the influence of the down deflection of the spoiler on the aerodynamic characteristics of the multi segment wing is studied.The result show that,the down deflection of the spoiler can significantly increase the lift and of the high lift configuration under the condition of the same slot parameters.With the increase angle of attack,both the flap down deflection configuration and the spoiler down deflection configuration attenuate the lift improvement,the attenuation of the spoiler down deflection configuration is more obvious.At 20°angle of attack,the spoiler down deflection configuration lift increment is about 15%of the 0°angle of attack,but at 20°angle of attack,the flap down deflection configuration lift increment is about 40%of the 0°angle of attack.

关 键 词：民用飞机 襟翼 ADHF 扰流板 

分 类 号：V224[航空宇航科学与技术—飞行器设计]