Abstract
© 2015, American Institute of Aeronautics and Astronautics Inc, AIAA. All Rights Reserved. An analytical solution to high-frequency gust-aerofoil interaction in background steady flow that is uniform far upstream is compared to numerical results for realistic aerofoils with non-zero thickness. Currently, numerical codes struggle at high frequencies, and are typically only validated against flat-plate analytical solutions. Analytical solutions presented in this paper for realistic aerofoil geometries are obtained using matched asymptotic techniques, and comparison with numerical solutions not only validates the numerical codes, but also confirms the validity of the analytical solution and its accuracy. Particular attention is given to the unsteady Kutta condition at the trailing edge, which is neglected in one numerical solution discussed in this paper; if the singularity in the surface pressure is incorporated into the analytical solution, the agreement between this numerical solution and the analytical solution is improved. Analytical solutions for the turbulent pressure spectrum close to the stagnation point of a thick aerofoil in uniform flow in both highand low-frequency regimes are also presented, and are seen to be in good agreement with experimental data.
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