摘要: This study presents aerodynamic and aeroacoustic measurements on the 30P30N high-lift airfoil in the newly commissioned hybrid anechoic wind tunnel at the University of Toronto. The hybrid wind tunnel test section is configured wi... 展开 This study presents aerodynamic and aeroacoustic measurements on the 30P30N high-lift airfoil in the newly commissioned hybrid anechoic wind tunnel at the University of Toronto. The hybrid wind tunnel test section is configured with Kevlar side walls to allow for simultaneous measurement of aerodynamic and acoustic quantities. Measurements were collected at geometric angles of attack from 0° to 15° and Mach numbers from 0.09 to 0.15. The mean pressure coefficient distribution agreed with measurements from similar models in other Kevlar-walled wind tunnels. Furthermore, the mean pressure coefficient distribution measured in the hard-wall configuration of the wind tunnel agrees with our CFD simulations and is used to estimate the aerodynamic corrections for the hybrid test section. Unsteady surface pressure measurements were taken in selected regions of the slat, main element, and flap and were consistent with existing literature, providing insight into the noise-generating mechanisms of the 30P30N airfoil. In consonance with the literature, the far-field noise spectra exhibited narrow-band mid-frequency tonal peaks around a Strouhal number (based on the slat chord) of St_s = 1.5 - 4.5. These tonal peaks and the broadband noise levels decrease with the angle of attack and have a Mach number to the power 4.5 (M~(4.5)) scaling. Noise source maps obtained from a phased microphone array using the frequency domain Delay-and-Sum beamforming algorithm show that the slat is the dominant noise source in the 1 to 8 kHz frequency range. In contrast, parasitic junction noise dominates at higher frequencies. 收起