Advanced search
Start date
Betweenand
Related content
(Reference retrieved automatically from Web of Science through information on FAPESP grant and its corresponding number as mentioned in the publication by the authors.)

Trailing-Edge Noise Predictions Using Compressible Large-Eddy Simulation and Acoustic Analogy

Full text
Author(s):
Wolf, William R. [1] ; Lele, Sanjiva K. [2, 1]
Total Authors: 2
Affiliation:
[1] Stanford Univ, Dept Aeronaut & Astronaut, Stanford, CA 94305 - USA
[2] Stanford Univ, Dept Mech Engn, Stanford, CA 94305 - USA
Total Affiliations: 2
Document type: Journal article
Source: AIAA JOURNAL; v. 50, n. 11, p. 2423-2434, NOV 2012.
Web of Science Citations: 9
Abstract

The present investigation of airfoil trailing-edge noise generation and propagation concerns the broadband noise that arises from the interaction of turbulent boundary layers with the airfoil trailing edge and the tonal noise that arises from vortex shedding generated by laminar boundary layers. Large-eddy simulations are conducted for a NACA0012 airfoil with rounded trailing edge for two flow configurations with different freestream Mach numbers (M-infinity = 0.115 and 0.4) for an angle of incidence of 5 deg. The Reynolds number based on the airfoil chord is fixed at Re-c = 408, 000. The acoustic predictions are performed by the Ffowes Williams and Hawkings acoustic analogy formulation and incorporate convective effects. Surface and volume integrations of dipole and quadrupole source terms appearing in the Ffowes Williams and Hawkings equation are performed using a three-dimensional wideband multilevel adaptive fast multipole method to accelerate the calculations of aeroacoustic integrals. The effects of Mach number and nonlinear quadrupole sources are assessed. Nonlinear quadrupole noise sources play an important role in far-field sound radiation for the higher Mach number flow configuration, M-infinity = 0.4. A scaling study is performed and, although surface pressure spectra scale with hydrodynamic scaling, far-field acoustics has a more complex behavior. The broad vortex-shedding tone generated by the laminar boundary layer vortex shedding noise causes a departure from the classical fifth power-law scaling, a behavior also seen in previous experiments. (AU)

FAPESP's process: 11/12493-6 - Investigation of Airfoil Self-Noise Generation and Propagation Using Large Eddy Simulation, Analytical Models and Acoustic Analogy
Grantee:William Roberto Wolf
Support Opportunities: Scholarships in Brazil - Post-Doctoral