This paper presents results of an empirical study on the flow and noise generated by the trailing edge of a flat plate encountering low turbulence fluid flow. Simultaneous measurements of flow and far-field noise data have been taken in an anechoic wind tunnel at the University of Adelaide. Velocity data about the trailing edge and in the wake have been measured using hot-wire anemometry. These data are related to far-field noise measurements obtained with two microphones: one mounted above and one mounted below the trailing edge. Spectral maps of the fluctuating velocity about the trailing edge are also presented. Experimental data of this kind provides further insight into the trailing edge noise mechanism and can be used to validate theo...
The noise generation of turbulent flows at the trailing edges of airfoils is a general design proble...
If technology such as aircraft, submarines and wind turbines are to further reduce their noise emiss...
The aerodynamic and acoustic testing of a NACA0012 airfoil section was performed in an open wind tun...
This paper presents an acoustic analysis of the noise generated at the trailing edge of a flat plate...
This paper presents results of a comprehensive empirical study on the flow and noise generated by th...
This paper presents an experimental study of the trailing edge noise produced by sharp-edged flat pl...
Airfoils operating at low-to-moderate Reynolds number may produce noise that contains one or more hi...
This paper presents experimental data concerning the flow and noise generated by a sharp-edged flat ...
Paper AIAA 2012-2186This paper presents the results of an experimental investigation exploring the n...
The noise generation of turbulent flows near the edges of airplanes and automobiles is a general des...
The noise generation of turbulent flows near the edges of airplanes and automobiles is a general des...
The efficient computation of turbulent airfoil trailing edge noise is important for the cost-effecti...
The feasibility of aeroacoustic noise predictions based on Particle Image Velocimetry (PIV) measurem...
© 2016, © The Author(s) 2016. The aerodynamic and acoustic testing of a NACA0012 airfoil section was...
This paper presents an experimental study on the noise reduction potential of sawtooth trailing edge...
The noise generation of turbulent flows at the trailing edges of airfoils is a general design proble...
If technology such as aircraft, submarines and wind turbines are to further reduce their noise emiss...
The aerodynamic and acoustic testing of a NACA0012 airfoil section was performed in an open wind tun...
This paper presents an acoustic analysis of the noise generated at the trailing edge of a flat plate...
This paper presents results of a comprehensive empirical study on the flow and noise generated by th...
This paper presents an experimental study of the trailing edge noise produced by sharp-edged flat pl...
Airfoils operating at low-to-moderate Reynolds number may produce noise that contains one or more hi...
This paper presents experimental data concerning the flow and noise generated by a sharp-edged flat ...
Paper AIAA 2012-2186This paper presents the results of an experimental investigation exploring the n...
The noise generation of turbulent flows near the edges of airplanes and automobiles is a general des...
The noise generation of turbulent flows near the edges of airplanes and automobiles is a general des...
The efficient computation of turbulent airfoil trailing edge noise is important for the cost-effecti...
The feasibility of aeroacoustic noise predictions based on Particle Image Velocimetry (PIV) measurem...
© 2016, © The Author(s) 2016. The aerodynamic and acoustic testing of a NACA0012 airfoil section was...
This paper presents an experimental study on the noise reduction potential of sawtooth trailing edge...
The noise generation of turbulent flows at the trailing edges of airfoils is a general design proble...
If technology such as aircraft, submarines and wind turbines are to further reduce their noise emiss...
The aerodynamic and acoustic testing of a NACA0012 airfoil section was performed in an open wind tun...