Abstract
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 3-dimensional aircraft configurations during the ongoing flow computation. The procedure is applied to a two-dimensional three-element high-lift airfoil configuration which is characterized by the existence of laminar separation bubbles using different operation modes of the procedure.
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Krumbein, A., Krimmelbein, N. (2007). Navier-Stokes High-Lift Airfoil Computations with Automatic Transition Prediction Using the DLR TAU Code. In: Tropea, C., Jakirlic, S., Heinemann, HJ., Henke, R., Hönlinger, H. (eds) New Results in Numerical and Experimental Fluid Mechanics VI. Notes on Numerical Fluid Mechanics and Multidisciplinary Design (NNFM), vol 96. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-540-74460-3_26
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DOI: https://doi.org/10.1007/978-3-540-74460-3_26
Publisher Name: Springer, Berlin, Heidelberg
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