Abstract
As illustrated in Chap. 3, Sect. 3.8.2, the unsteady pressure on the nose of an aerofoil during gust-aerofoil interaction in uniform flow was predicted to be singular, which violates the small perturbation assumption, and hence the asymptotic results become invalid in a small region close to the nose of the aerofoil.
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Ayton, L. (2015). Leading-Edge Stagnation-Point Noise Generated by Turbulence in Subsonic Uniform Flow. In: Asymptotic Approximations for the Sound Generated by Aerofoils in Unsteady Subsonic Flows. Springer Theses. Springer, Cham. https://doi.org/10.1007/978-3-319-19959-7_5
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