Abstract：Experimental research and simulation analysis are performed on aeroacoustic noise characteris-tics of an aircraft’s main landing gear component in this paper. The sound field radiated from the model is measured in the aeroacoustic wind tunnel at different wind speeds. The noise spectra are evaluated by the mi-crophones. Detached Eddy Simulation is used to produce the flow field of the model. The source strength and location are determined though the vortex sounds theory. The acoustic field is calculated via FW-H equation. The frequency spectra, the directivity characteristics and the noise mechanism are subsequently studied. The results indicate that the low and the middle spectra from the simulation agree with that from the experiment. The noise radiated from the model is broadband noise. The spectra and dominant frequencies increase with the incensement of the wind speed. In the spectra there are two energy peaks which are corresponding to the inter-action noise between shock absorber and strut, shock absorber and bogie, respectively. The pressure fluctuation which forms the noise sources is on the down surface of the shock absorber. The shock absorber and bogie is main contributor while the strut is the least contributor to the total noise. Noise radiation has dissymmetric directivities.
2013, Vol. 32 
