A Reynolds-averaged Navier-Stokes solver, a laminar boundary-layer code and different transition prediction methods for the prediction of Tollmien-Schlichting and cross flow instabilities were coupled for the automatic prediction of laminar-turbulent transition on general three-dimensional aircraft configurations during the ongoing flow computation. In this article, the procedure is applied to a two-dimensional three-element high-lift airfoil configuration which is characterized by the existence of laminar separation bubbles. The automatic transition prediction procedure is applied using different operation modes and different transition prediction strategies.


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    Krumbein, A. | British Library Conference Proceedings | 2009


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