某验证机角隅分离数值计算及优化  

Numerical simulation and optimization of junction separation for a verification aircraft

作　　者：魏自言 李杰[1] 杨钊 WEI Ziyan;LI Jie;YANG Zhao(School of Aeronautics,Northwestern Polytechnical University,710072 Xi'an,China)

机构地区：[1]西北工业大学航空学院,西安710072

出　　处：《应用力学学报》2025年第1期29-39,共11页Chinese Journal of Applied Mechanics

基　　金：国家自然科学基金资助项目(No.11972304,91952302)。

摘　　要：飞机部件结合处易诱导产生角隅流动结构,尤其对于T型垂尾飞机,在小侧滑角状态下产生角隅流动产生分离可能导致飞机航向静不安定。利用基于二次本构关系(quadratic constitutive relation,QCR)的k-ω SST方法针对Rood翼型标模进行计算以验证k-ω SST-QCR方法计算精度,并对某验证机平垂尾结合处的角隅分离进行整流,抑制其由于平尾及垂尾的边界层在结合处交汇后复杂的相互作用所引起的流动分离,使平垂尾结合处在小侧滑角状态下无分离流动。结果表明垂尾背风面的分离流动是航向静不安定的主要原因,通过对平垂尾结合处采用整流锥修型,显著抑制了角隅流动分离,使其在小侧滑角状态恢复航向静安定。The junction flow separation structure can be induced at the junction of aircraft components.Especially for a T-type tail aircraft,the junction separation flow may lead to directional instability under small sideslip angle.The k-ω SST-QCR method is used to analyze the corner separation at the T-type tail junction of a verify aircraft,and to suppress the flow separation caused by the complex interaction of the boundary layer.Results show the separation flow on the leeward side of the vertical tail causes the directional instability.The corner flow separation can be suppressed by using the fairing cone at the junction,so that the aircraft can maintain the directional stability at a small sideslip angle.

关 键 词：角隅分离 二次本构关系 翼身结合 流动控制 航向静安定 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]