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Numerical Computation of Unsteady Compressible Flow past a Plunging Aerofoil
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نویسنده
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Kumar K. S. ,Sajjan S. V.
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منبع
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journal of applied fluid mechanics - 2012 - دوره : 5 - شماره : 4 - صفحه:131 -138
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چکیده
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Unsteady reynolds-averaged navier-stokes (rans) computations are presented for subsonic and transonic flow past a plunging naca 64a010 aerofoil. the implicit rans solver used for obtaining the time-accurate solution is based on finite volume nodal point spatial discretization scheme with dual time stepping. results for the subsonic and transonic cases compare well with the experimental data, thus demonstrating the capability of the solver to provide useful unsteady pressure data for aeroelastic analysis.
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کلیدواژه
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Viscous flow ,RANS solver ,Implicit method ,Heaving aerofoil ,Nodal point scheme
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آدرس
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Council of Scientific and Industrial Research, National Aerospace Laboratories, Computational and Theoretical Fluid Dynamics Division, India, Council of Scientific and Industrial Research, National Aerospace Laboratories, Computational and Theoretical Fluid Dynamics Division, India
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Authors
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