后掠翼对细长体中段大迎角绕流的影响  

Influence on flow around mid-part of slender at high AOA by sweep wing

作　　者：李国辉[1] 邓学蓥[2] 

机构地区：[1]空军航空大学军事仿真技术研究所,长春130022 [2]北京航空航天大学航空科学与工程学院,北京100083

出　　处：《北京航空航天大学学报》2007年第1期1-4,9,共5页Journal of Beijing University of Aeronautics and Astronautics

基　　金：航空基础科学基金资助项目(02A5148)

摘　　要：采用在细长体顶点处添加扰动块的方式使细长体的绕流具有确定性．研究了在大迎角下，后掠翼对细长体绕流结构和气动力特性的影响．实验结果表明，在30°迎角时，细长体中段背风侧的流动和压力分布受到后掠翼与头部背涡的双重控制．在迎角a=40°-60°范围内，后掠翼对细长体中段绕流起主控作用，使细长体中段背风侧流动呈现完全分离流状态，使得中段背风侧的压力分布保持为均值．The flow around a slender was fixed in this way which a tiny perturbation was located on the nose of the slender. The influence on flow structure and aerodynamic of a slender by sweep wing at high angle of attack was studied. The experimental results indicate that at angle of attack 30° ,the flow and pressure distribution of mid-part leeside of a slender are dominated by sweep wing and forebody vortices. At angles of attack et = 40°-60°, sweep wing dominates the flow around the mid-part of a slender only, and the flow of midpart leeside of a slender becomes full separate flow, the pressure distribution of mid-part leeside of a slender retains constant.

关 键 词：细长体 大迎角空气动力学 后掠翼 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]