COMPUTATIONAL AEROACOUSTIC PREDICTION OF TRANSONIC ROTOR NOISE BASED ON REYNOLDS- AVERAGED NAVIER-STOKES FLOW SIMULATION

摘要

An efficient and accurate method for predicting the aeroacoustic noise generated by transonic helicopter rotors is investigated. The near-field noise is calculated by numerically solving Reynolds-Averaged Navier-Stokes (RANS) equations using chimera grid methodology. The far-field noise is predicted by using the method based on Ffowcs Williams-Hawkings equation with penetrable data surface (FW-H_(pds)) covering the nonlinear flow region. The computed results are compared with experimental data and good agreement has been achieved. The results are also compared with that of the method based on inviscid flow simulation using Euler equations. It shows that the present method is more accurate for the prediction of High-Speed Impulsive (HIS) noise generated by transonic helicopter rotors.