摘要
主要介绍了翼身组合体模型在CARDC-Φ3.2m亚声速风洞进行非定常气动特性研究。研究内容包括一60°后掠角三角翼身组合体在俯仰和滚转振荡中的气动特性,以及展向吹气对动态气动特性的影响。另外,运用PIV技术研究了非定常气动特性及展向吹气影响的流动机理。研究结果表明:利用展向吹气可显著改善在俯仰和滚转振荡中气动特性的迟滞现象。
In this paper measurement results and analysis concerned with unsteady aerodynamics characteristics and vortex flow over a delta wing and fuselage combinations are presented. The experiment was conducted in Dia3.2 meter subsonic wind tunnel of CARDC. The unsteady aerodynamics characteristics during large amplitude pitching and rolling oscillation were measured respectively. PIV technique was applied in the test to obtain velocity and vorticity field. In addition, using the spanwise blowing to control the vortex separation is also investigated. The experimental results indicate that the spanwise blowing could effectively control the vortex separation, improve the maximum lift coefficient and increase the stall angle-of-attack.
出处
《流体力学实验与测量》
CSCD
北大核心
2004年第3期50-54,74,共6页
Experiments and Measurements in Fluid Mechanics
基金
国防科技预研跨行业基金(00J13 1 3 KG2913)
