Numerical Study of Noise Sources Generated by Wing of Supersonic Business Jet in Landing Mode

The paper is devoted to the numerical study of wing noise for the prototype of supersonic business jet in landing mode. Near the wing, the acoustics is simulated using the CFD/CAA methods within the Delayed Detached Eddy Simulation approach. The Ffowcs Williams–Hawkings method is used for calculation of noise radiation in the far field. To localize the near-field acoustic sources, the advanced postprocessing including the numerical beamforming method is applied. The numerical beamforming formulated for monopole- and dipole-type sources allowed for detecting the main sources of the wing noise in the vicinity of leading and trailing edges. Analysis of the sound pressure level calculated for signals recorded on the Ffowcs Williams–Hawkings surface during the CFD simulations generally confirmed these results. Direct comparison of the noise spectra calculated by the Ffowcs Williams–Hawkings and numerical beamforming methods is provided for selected mid-field points. According to the presented noise radiation pattern, the far-field noise generated by the considered wing in landing mode has dominating dipole-type component for frequencies lower than 250 Hz and dominating monopole-type component for frequencies higher than 1 kHz.