Abstract
Simulation of sound wave propagation at the inlet of a jet engine is difficult due to the complex geometries of the propagation channel, so many simplifications are needed. A more realistic model is introduced in this paper to do the simulation. Dispersion-relation-preserving finite schemes are used in this paper where structured grids are designed by conformal mapping; the advanced perfectly matched layer absorbing boundary conditions are used to prescribe the input sound wave at the fan face of inlet. The advantages of the methods used in this paper are shown by two different cases.
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