NOISE REDUCTION OF A TILT-ROTGR AIRCRAFT INCLUDING EFFECTS ON WEIGHT AND PERFORMANCE

摘要

Various methods for far-field noise reduction of a tilt-rotor acoustic signature and the performance and weight tradeoffs, which result from modification of the noise sources are considered in this report. In order to provide a realistic approach for the investigation, the Boeing Tilt-Rotor Flight Research Aircraft (Model 222 as defined in Ref. 1) was selected as the baseline. This aircraft has undergone considerable engineering development. Its rotor has been manufactured and tested in the Ames full-scale wind tunnel. Therefore, the study reflects the current state-of-the art of aircraft design for far-field acoustic signature reduc¬tion and is not based solely on an engineering feasibility (paper) aircraft. This report supplements a previous study investigating reduction of noise signature through the management of the terminal flight trajectory (Ref. 2).