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Descripción
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| Delaying laminar to turbulent transition is of crucial importance for the aeronautics industry, since the friction drag in turbulent regime is considerably higher than in the laminar one. Several procedures have been reported for the purpose of transition delay, with the objective of reducing fuel consumption and contaminant emission. One of the most promising strategies is the boundary layer suction, listed on top of the technological readiness level of laminar flow control methods. In this work, a numerical study is presented for the compressible flow around an infinite swept wing in the presence of boundary layer suction. This flow control method is modeled as a boundary condition, imposing the wall normal velocity component on the wing surface. The suction slots include gaps to represent a real situation where manufacturing constraints lead to an unfeasible infinite or continuous setting. It is also investigated the different geometric configurations of suction slots to analyze the effectiveness of this stabilizing method in order to identify the existence of an optimal suction pattern. This study includes the solution of the pressure field over a swept wing using the Reynolds Averaged Navier-Stokes equations, plus the three-dimensional boundary layer solution and the posterior instability analysis of the resulting base flow using the three-dimensional Parabolic Stability Equations. The fully 3d numerical method is employed to predict the disturbance growth and to show the stabilization effect of suction upon the crossflow modes in a wide range of frequencies and wave numbers, and to reveal, for a fixed suction intensity, the existence of a optimal suction layout in which the stabilization effect is maximised. | |
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Internacional
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Si |
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Nombre congreso
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DiPaRT2016 Flight Physics Symposium |
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Tipo de participación
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960 |
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Lugar del congreso
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Bristol, UK |
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Revisores
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Si |
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ISBN o ISSN
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DOI
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Fecha inicio congreso
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21/11/2016 |
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Fecha fin congreso
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23/11/2016 |
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