Overview

During a flight test study of the noise effects on laminar flow on the outside surface of a simulated engine nacelle, an intense acoustic response was observed. The aircraft speed at which this signal occurred and the frequency content of the signal fell within the test conditions of the experiment and had to be eliminated prior to continuing. The signal was identified as an aerodynamic excitation of an acoustic mode in the simulated by-pass duct of the nacelle. By modifying the trailing edges of the support struts of the nacelle, the aerodynamic excitation was changed enough to eliminate the resonant response of the offending duct modes, eliminating the unwanted acoustic problem. Schoenster, James A. Langley Research Center NASA-TM-102585, NAS 1.15:102585 RTOP 506-80-31-06...

Full Product Details

9781725008779

Table of Contents

Reviews

Author Information

Tab Content 6

Countries Available