R= outer radius of the engine's secondary exhaust T= acoustical source period Uexhaust o=
steady mean-field flow, in the exhaust vicinity Uairfoil o= steady mean-flow field, in the airfoil …

THE noise environment around airports is a major cause of concern worldwide, with many
local communities exposed to high levels of aircraft noise; the effective reduction of such a …

Nowadays, computational aeroacoustics (CAA) is used for simulating wave propagation in
ducted turbofans, especially as computational fluid dynamics (CFD) is increasingly …

Fan noise generated by rotor-stator interaction mechanisms is the major tone source
component of high-bypass ratio aeroengines during take-off and approach conditions1. A …

View Video Presentation: https://doi. org/10.2514/6.2021-2167. vid A two-way coupled
DG/FM-BEM method is applied for computing fan tone shielding for various aircraft …

BPF= blade passing frequency kR= reduced frequency (with respect to the outer radius of
the engine secondary exhaust) Μ∞= steady mean-flow Mach number (at infinite) Μ inj …

I. Introduction he noise generated by an aircraft in approach configuration has two main
contributions, firstly the airframe noise resulting from turbulent flows over solid structures like …

The main objective of this paper is the characterization of the fan noise radiated in the aft
direction for a coaxial turbofan installed in RFN (Rear Fuselage Nacelle) position. The …

BPF= blade passing frequency kR= reduced frequency (with respect to the outer radius of
the engine secondary exhaust) λ, λ*= wavelength, and apparent wavelength Μ∞= steady …

13th AIAA/CEAS Aeroacoustics Conference (28th AIAA Aeroacoustics Conference) :
Numerical Study of 3D Acoustic Installation Effec Page 1 American Institute of Aeronautics …