翼身组合体大迎角前体非对称涡流动性态研究  

The study of evolution of the flow over the wing-body combination along the model axis at high incidences

作　　者：陈莹[1] 邓学蓥[1] 王延奎[1] 黄涛[1] 

机构地区：[1]北京航空航天大学流体所,北京100083

出　　处：《空气动力学学报》2007年第4期454-460,共7页Acta Aerodynamica Sinica

基　　金：国家自然科学基金资助项目(10172017和10432020);翼型叶栅空气动力学国防科技重点实验室基金资助项目(51462020504HK0101)

摘　　要：在亚临界流动范围内,对于带有鸭翼、机翼的翼身组合体,在其头尖部带有确定扰动的条件下,研究模型大迎角下的非对称背涡结构及其气动力特性随扰动周向角的演化规律。通过对模型表面的压力分布和侧向力分布分析,结合流场显示结果,表明翼身组合体绕流中鸭翼前各截面均处于非对称二涡区,头部截面侧向力分布随头尖部滚转而呈现出双稳态特性,鸭翼和机翼上方的流动在大迎角下处于完全分离流动状态,从而使得模型上鸭翼之后的截面侧向力接近为零。The behaviors＇of forebody asymmetric vortices with the manual perturbation on the nose tip and their eorresponding aeredynamic characteristics over the wing-canard-body combination have been studied at high angles of attack in the sub-critical Reynolds numbers range. It is indicated from the sectional pressure distributions and the sectional side force distributions on the model that the asymmetric vortices flow over the forebody of the wing-body is in the twin asymmetric vortices flow regime. And this twin asymmetric vortices and side force behavior appear the bi-stable state character. However the flow over the model after forebody including the canard and wings is in the full separated flow region at the high angle of attack and it is no longer influenced by the nose manual perturbation. Therefore it is clearly indicated that the source of side force on the model of wing-body combination is mainly from twin asymmetric vortices over the forebody rather than afterbody including canard and wing.

关 键 词：翼身组合体 非对称涡流动 双稳态 分离流 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]