EXPERIMENTAL STUDY ON THE BUFFET PHENOMENON OF NACA0012 AIRFOIL

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.