Abstract
In the past several years, considerable advances have been made in the prediction of transonic trailing-edge flows. For modern supercritical airfoils the trailing edge region is dominated by viscous-inviscid interaction. In the near wake the flow field is complicated by streamline curvature and due to the interaction of the merging of two significantly different shear layers. Integral boundary-layer methods coupled with an inviscid flow-field solution have been successfully applied to both symmetric and asymmetric trailing-edge flows provided there is no boundary layer separation [128, 217, 218]. These methods are not satisfactory for flows with strong adverse pressure gradients leading to significant separated regions [217, 219]. Differential methods employing either a boundary-layer code coupled with an inviscid solution or the mass-averaged Navier—Stokes equations throughout the flow field have also been successful provided separation was not present [210, 218]. Recently an asymmetric trailing-edge flow with a small separated zone was successfully predicted using the Navier—Stokes equations [220]. The ability to calculate trailing-edge flows with large separated zones remains to be tested.
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© 1984 Springer Science+Business Media New York
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Horstman, C.C. (1984). Numerical Simulation of Turbulent Trailing Edge Flows. In: Cebeci, T. (eds) Numerical and Physical Aspects of Aerodynamic Flows II. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-662-09014-5_6
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DOI: https://doi.org/10.1007/978-3-662-09014-5_6
Publisher Name: Springer, Berlin, Heidelberg
Print ISBN: 978-3-662-09016-9
Online ISBN: 978-3-662-09014-5
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