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Dynamic analysis of aeroacoustic hysteresis of a low-Reynolds-number airfoil
Phys. Rev. Fluids 7, 094401 – Published 26 September, 2022
DOI: https://doi.org/10.1103/PhysRevFluids.7.094401
Abstract
Lifting surfaces in aerospace and power industry applications produce tonal noise at low-to-medium Reynolds number, significantly contributing to global noise annoyance. The dominant noise frequency depends on the freestream velocity, angle of attack, and surrounding environment. This work reports that the frequency spectra can exhibit different behavior at the same flow condition, which constitutes the hysteresis phenomenon. Time-resolved particle image velocimetry (PIV) of boundary-layer flows near the trailing edge and far-field noise measurements are performed simultaneously and synchronously. Two branches of experiments are conducted with the freestream velocity increasing and decreasing, respectively. Results are analyzed from the perspective of modern dynamical systems. The boundary layer is viewed as the forced oscillator, with the acoustic waves being the forcing mechanism. Both the bifurcation theory and the Poincaré section are introduced to investigate the dynamic process when freestream velocity changes. Typically, the dominant frequency of acoustic waves matches that of the most amplified disturbances in the boundary layer, which is consistent with existing literature on the same noise generation mechanism. However, dual peaks can be observed at specific freestream velocities: one matches the natural frequency of the current flow state while the other matches that of the previous state. The associated transitions between periodic and quasiperiodic oscillations constitute the hysteresis phenomenon.
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