Navier-Stokes High-Lift Airfoil Computations with Automatic Transition Prediction Using the DLR TAU Code-Reference-Cited by-同舟云学术

Navier-Stokes High-Lift Airfoil Computations with Automatic Transition Prediction Using the DLR TAU Code

Published: Issue: Volume: Page:210-218
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Container-title:Notes on Numerical Fluid Mechanics and Multidisciplinary Design (NNFM)
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Author:

Krumbein A.,Krimmelbein N.

Publisher

Springer Berlin Heidelberg

Link

http://link.springer.com/content/pdf/10.1007/978-3-540-74460-3_26.pdf

Reference14 articles.

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2. Smith, A.M.O., Gamberoni, N., ”Transition, Pressure Gradient and Stability Theory”, Douglas Aircraft Company, Long Beach, Calif. Rep. ES 26388, 1956.

3. van Ingen, J.L., ”A suggested Semi-Empirical Method for the Calculation of the Boundary Layer Transition Region”, University of Delft, Dept. of Aerospace Engineering, Delft, The Netherlands, Rep. VTH-74, 1956.

4. Kroll, N., Rossow, C.-C., Schwamborn, D., Becker, K., and Heller, G, ”MEGAFLOW — A Numerical How Simulation Tool For Transport Aircraft Design”, ICAS Congress 2002 [CD-Rom], ICAS, Toronto, Canada, 2002, pp. 1.105.1–1.105.20.

5. Nebel, C., Radespiel, R., and Wolf, T., ”Transition Prediction for 3D Hows Using a Reynolds-Averaged Navier-Stokes Code and N-Factor Methods”, AIAA-2003-3593.

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3. Hybrid RANS/LES Simulations of a Three-Element Airfoil;Progress in Hybrid RANS-LES Modelling;2012

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