Computational study of boundary layer effects on stochastic rotor blade vortex shedding noise
Author:
Funder
Langley Research Center
NASA Aeronautics Research Mission Directorate
National Aeronautics and Space Administration
Ames Research Center
Publisher
Elsevier BV
Subject
Aerospace Engineering
Reference42 articles.
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4. Experimental investigations of a trailing edge noise feedback mechanism on a NACA 0012 airfoil;Plogmann;Exp. Fluids,2013
5. Regimes of tonal noise on an airfoil at moderate Reynolds number;Pröbsting;J. Fluid Mech.,2015
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