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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。
A dynamic pressure sensor was used to measure the fluctuating pressure in the sidewall of the wind tunnel. The experimental study of the transonic vibration at zero angle of attack was carried out for the NACA0012 airfoil. The airfoil pressure along the chord and span direction distributed. The pulsating pressure results are analyzed from the time domain and the frequency domain. The chattering characteristics of the NACA0012 airfoil, such as the initial Mach number and chattering frequency, are obtained. The results show that the two-dimensional wind tunnel has good two-dimensional characteristics and the pressure in the side wall can reflect the changes of the pressure in the core stream. The chattering occurs in the range of Maexp = 0.88-0.89. With the increase of Mach number, The vibration frequency has increased.