Numerical Study on Acoustic Emission from Flow Past an Airfoil

概要

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The sound pressvrre level is computed using the Lighthill-Curie theory for the far-field acousticpressure excited by flow around solid bodies. Time evolvrtion of the flow field is obtained bysolving the three-diznensional conapressible Navier-Stokes eqtration with a block pentadiagonalmatrix scheme based on the approximttte f'actorization naethod. The far-field sound pressurelevel is evaluated from the fluctttation of the pressure on a wing surface. Nurnerical simulation isdone for a NACA-0015 airfoil at the attack angle of 8' in a subsonic flow. The computed resultsare compared successfully with the experinaental data. The sturface dipole strength density ises'timated to show which regions in space donainantly contriloute to prouninent peaks in the sotmndpressure level. We discuss the three-diznensional effect by cottaparing the results from the three-and two-dimensional computation.
社団法人日本物理学会の論文
1997-07-15