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NACA0012翼型抖振现象实验研究 被引量:6

EXPERIMENTAL STUDY ON THE BUFFET PHENOMENON OF NACA0012 AIRFOIL
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摘要 通过在风洞侧壁安装动态压力传感器测量侧壁脉动压力的方法针对NACA0012翼型开展了零攻角状态下跨声速抖振特性的实验研究,并测量了翼型沿弦向与展向的压力分布。从时域和频域两个方面分析了脉动压力结果,得到了NACA0012翼型的跨声速抖振起始马赫数和抖振频率等抖振特性。研究结果表明:风洞二维性较好,侧壁区域的压力情况能够反映核心流压力变化情况;抖振发生在实验马赫数Maexp=0.88~0.89范围内;随着马赫数的增大,抖振频率有所增加。 Experimental study of NACA0012 airfoil transonic buffet characteristics at zero angle of attack was conducted in the NF-6 transonic wind tunnel. The dynamic pressure was measured at the side wall by dynamic pressure transducers, and the static pressure was also measured along the streamwise and spanwise. The pressure fluctuation results at the side wall were presented both in time domain and frequency domain, and the transonic buffet onset Mach number and buffet frequency were obtained. The results show that the flow field can keep two dimensionality along the spanwise, so that the dynamic pressure measured at the side wall can reflect the characteristics of the buffet. The NACA0012 airfoil buffet occurs in a narrow brand of Mach number from 0.88 to 0.89 at zero angle of attack and the buffet frequency increases slightly with increasing Mach number.
出处 《工程力学》 EI CSCD 北大核心 2015年第5期236-242,共7页 Engineering Mechanics
基金 国家重点实验室研究基金项目(9140C420301110C42) 西北工业大学基础研究基金项目(JC201103) 航空科学基金项目(2013ZD53057)
关键词 翼型 跨声速抖振 激波附面层干扰 风洞实验 固定转捩 airfoil transonic buffet shock wave boundary layer interference wind tunnel experiment fixed transition
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