A study of wall pressure fluctuations beneath turbulent boundary layers was carried out at a flat plate configuration in the Aeroacoustic Wind Tunnel Braunschweig. The wall fluctuating pressure was measured by flush-mounted Kulite sensors. Boundary layer mean velocities were measured by a single-wire hot-wire anemometer. Through installing a NACA 0012 airfoil above the plate, a pressure gradient distribution can be produced on the plate flow. By changing the streamwise position and the angle of attack of the airfoil, a different upstream flow development can be realized. The effect on the wall pressure spectra by different upstream histories is studied. The spectral attenuation caused by the flush-mounted sensor is discussed. A new correction is proposed and compared to the Corcos correction. Furthermore, artificial flow disturbance was made to investigate the impact of the disturbance on the measured wall pressure spectra. The robustness to flow disturbance was also tested for different boundary layer conditions.
展开▼
