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.)

Leading-Edge Noise Prediction of General Airfoil Profiles with Spanwise-Varying Inflow Conditions

Full text
Author(s):
Miotto, Renato F. [1] ; Wolf, William R. [1] ; de Santana, Leandro D. [2]
Total Authors: 3
Affiliation:
[1] Univ Estadual Campinas, Dept Energy, BR-13083860 Campinas, SP - Brazil
[2] Univ Twente, Fac Engn Technol, Drienerlolaan 5, NL-7522 NB Enschede - Netherlands
Total Affiliations: 2
Document type: Journal article
Source: AIAA JOURNAL; v. 56, n. 5, p. 1711-1716, MAY 2018.
Web of Science Citations: 2
Abstract

This paper presents a study of the leading-edge noise radiated by an airfoil undergoing a turbulent inflow. The noise prediction of generic airfoil profiles subjected to spanwise-varying inflow conditions is performed with the support of Amiet's theory and the inverse strip technique. In the proposed methodology, the aeroacoustic transfer function of a generic airfoil profile is computed by the boundary element method. The effects of the airfoil leading-edge thickness on the inflow turbulence are accounted for by a turbulence spectrum based on the rapid distortion theory. This research shows that the turbulence distortion plays a significant role on the predicted noise levels. Compared with the von Karman model for isotropic turbulence, the rapid distortion theory predicts reduced noise levels at high frequencies and increased noise levels at low frequencies. This paper also shows that the spanwise-varying inflow, here represented by a linearly changing condition, contributes to raising the noise levels when compared to the similar uniform inflow case. This research confirms that the finite airfoil thickness decreases the airfoil-gust lift response, consequently reducing the noise levels. This observation is more pronounced for microphones positioned downstream of the airfoil and for high frequencies. (AU)

FAPESP's process: 15/19538-6 - Application of computational aeroacoustics for the investigation of acoustic diffraction effects along airfoil trailing edges
Grantee:Renato Fuzaro Miotto
Support Opportunities: Scholarships in Brazil - Master
FAPESP's process: 13/03413-4 - Investigation of noise generation and propagation by aerodynamic configurations using computational aeroacoustics
Grantee:William Roberto Wolf
Support Opportunities: Research Grants - Young Investigators Grants