Experiments in Fluids

, Volume 41, Issue 5, pp 777–788 | Cite as

Experimental investigation of a blunt trailing edge flow field with application to sound generation

  • Daniel W. ShannonEmail author
  • Scott C. Morris
Research Article


The unsteady lift generated by turbulence at the trailing edge of an airfoil is a source of radiated sound. The objective of the present research was to measure the velocity field in the near wake region of an asymmetric beveled trailing edge in order to determine the flow mechanisms responsible for the generation of trailing edge noise. Two component velocity measurements were acquired using particle image velocimetry. The chord Reynolds number was 1.9 × 106. The data show velocity field realizations that were typical of a wake flow containing an asymmetric periodic vortex shedding. A phase average decomposition of the velocity field with respect to this shedding process was utilized to separate the large scale turbulent motions that occurred at the vortex shedding frequency (i.e., those responsible for the production of tonal noise) from the smaller scale turbulent motions, which were interpreted to be responsible for the production of broadband sound. The small scale turbulence was found to be dependent on the phase of the vortex shedding process implying a dependence of the broadband sound generated by the trailing edge on the phase of the vortex shedding process.


Vorticity Particle Image Velocimetry Streamwise Velocity Turbulent Motion Turbulent Length Scale 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.



This research was made possible through funding from the US Office of Naval Research under Grant No. N00014-03-1-0105, Dr. Ron Joslin, program manager.


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Copyright information

© Springer-Verlag 2006

Authors and Affiliations

  1. 1.Department of Aerospace and Mechanical Engineering, B026 Hessert LaboratoryUniversity of Notre DameNotre DameUSA
  2. 2.Department of Aerospace and Mechanical Engineering, 109 Hessert LaboratoryUniversity of Notre DameNotre DameUSA

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