Stochastic estimation of flow near the trailing edge of a NACA0012 airfoil |
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Authors: | Ana Garcia-Sagrado and Tom Hynes |
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Institution: | (1) Whittle Laboratory, Department of Engineering, University of Cambridge, 1 JJ Thomson Avenue, Cambridge, CD3 0DY, UK;(2) Present address: Applied Modelling and Computation Group, Department of Earth Science and Engineering, Royal School of Mines, Imperial College London, Prince Consort Road, London, SW7 2BP, UK |
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Abstract: | A stochastic estimation technique has been applied to simultaneously acquired data of velocity and surface pressure as a tool
to identify the sources of wall-pressure fluctuations. The measurements have been done on a NACA0012 airfoil at a Reynolds
number of Re
c
= 2 × 105, based on the chord of the airfoil, where a separated laminar boundary layer was present. By performing simultaneous measurements
of the surface pressure fluctuations and of the velocity field in the boundary layer and wake of the airfoil, the wall-pressure
sources near the trailing edge (TE) have been studied. The mechanisms and flow structures associated with the generation of
the surface pressure have been investigated. The “quasi-instantaneous” velocity field resulting from the application of the
technique has led to a picture of the evolution in time of the convecting surface pressure generating flow structures and
revealed information about the sources of the wall-pressure fluctuations, their nature and variability. These sources are
closely related to those of the radiated noise from the TE of an airfoil and to the vibration issues encountered in ship hulls
for example. The NACA0012 airfoil had a 30 cm chord and aspect ratio of 1. |
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Keywords: | |
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