Abstract
Aeroacoustic simulation of a ring rotor in presence of a uniform inlet ow is presented. An unsteady RANS simulation with a compressible solver is used to compute the ow eld and identify the acoustic sources on the rotor. The tip clearance recirculation shows upstream vortices that appear to impact the rotor blades creating the main source of unsteadiness. Since those vortices rotate at a lower speed than the rotor, the impact frequency implied is shown to be di erent than the blade passing frequency. Besides the aerodynamic simulation, the acoustic signature of this rotor is computed by propagating the noise sources located on the rotor surfaces using two methods: a Ffowcs-Williams & Hawkings analogy in the time-domain, as well as an analytical model in the frequencydomain based on the compact rotating dipole formulation. A comparison with experimental results con rms the aeroacoustic phenomena are well captured and properly propagated by the acoustic codes.
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