The Prediction of Noise Scattered by a Wing/Ducted Fan Configuration

By: Nasa, National Aeronautics and Space Adm

In this proof of concept research, a computational method was developed for predicting the sound field created by the scattering of ducted fan engine noise by a blended wing-body (BWB). It was assumed that all acoustic processes were linear and time harmonic with excitation frequency co. Inflow effects were neglected and no penetration boundary conditions were applied to the engine nacelle and BWB surfaces. A scattering approach was adopted in which the total acoustic field is written as the sum of known incident (from the engine duct) and unknown scattered parts. We further assume that the incident field is independent of the scattered field. Application of the above conditions to the equations of linearized acoustics yields the Helmholtz equation (reduced wave equation) for the scattered pressure with Neumann boundary conditions.Tweed, John and Dunn, Mark H.Langley Research CenterAERODYNAMIC CONFIGURATIONS; BODY-WING CONFIGURATIONS; ENGINE NOISE; NOISE PREDICTION; SCATTERING; SOUND FIELDS; WAVE EQUATIONS; AIRCRAFT NOISE; ACOUSTIC SCATTERING; NEUMANN PROBLEM; EQUIVALENCE; TWO DIMENSIONAL MODELS; THREE DIMENSIONAL MODELS

• Format: Paperback
• Language: English
• ISBN: 1723768073
• ISBN13: 9781723768071
• Release Date: January 1
• Publisher: Independently Published
• Length: 36 Pages
• Weight: 0.24 lbs.
• Dimensions: 0.1" x 8.5" x 11.0"