| Citation: | XIAO Chunhua, CHE Binghui, TONG Fan. Experiment of the far-field acoustic characteristics of an airfoil with smooth rime ice model on the leading edge[J]. Journal of Aerospace Power, 2023, 38（10）：2328-2337 doi: 10.13224/j.cnki.jasp.20220242
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The relationship between ice thickness and aeroacoustic increment provides a new idea for exploring a new method of ice thickness detection. The far-field acoustic characteristics of a NACA0012 airfoil with smooth rime ice model on the leading edge were studied experimentally. The low-noise aeroacoustic wind tunnel of the University of Southampton was used as the experimental platform. The far-field noise signals were measured by a arc microphone array. The far-field sound pressure was processed by fast Fourier transform to obtain the effects of the maximum ice thickness, airflow speed and angle of attack on the sound pressure level of NACA0012 airfoil. The results showed that, the smooth rime ice model changed the local flow field around the leading edge of the airfoil, resulting in a relatively large variation of far-field acoustic characteristics by flow separation. The maximum increment of the far-field sound pressure level between iced airfoil and baseline exceeded 9.5 dB within the frequency between 8×103−2×104 Hz. There was a positive correlation between the maximum ice thickness, airflow speed, angle of attack and the far-field sound pressure level of iced airfoil. A neural network prediction model of maximum icing thickness with multivariable inputs such as flight parameters and overall sound pressure level increment was established.
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