Abstract
High-intensity acoustical disturbances can cause transition of controlled laminar flow. An investigation was made to determine whether main propulsion engines installed on an aircraft wing would cause excessive transition of laminar to turbulent flow. A method was developed for analyzing the influence of noise on the stability of a controlled laminar boundary layer, based upon the Tollmien–Schlichting traveling wave solution of the Orr–Sommerfeld equation and some wind tunnel experimental data. It is concluded that wing-mounted, high-bypass-ratio engines with sufficient acoustic treatment for controlling turbomachinery noise would not cause excessive loss of wing laminar flow. Additional analytical and experimental work is needed, however, to improve the accuracy of engine nearfield noise prediction, and the need to improve the proposed models to account for the acoustic transfer function for predicting transition.
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