Abstract
F OLLOWING Ffowcs-Williams and Hawkings' theory,' the three-dimensional quasi-steady fullpotential rotor flow analysis code ROT22, adapted from Jamesons' FLO22 code, is run in conjunction with the Farassat Noise code and the linear noise made by rotor blade in hover investigated. For the case considered, the study, while it confirms the earlier finding that the blade volume displacement is a dominant source of helicopter noise, contradicts a previously drawn conclusion namely that the blade tip loading makes a significant contribution to the overall noise. The thickness noise is further compared with the one calculated from the Schmitz-Yu code. It is shown that the inclusion of blade profile curvature in the calculations improves the negative peak amplitudes overpredicted by a Schmitz-Yu study.
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