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Transitionsvohersage für dreidimensionale Konfigurationen

The prediction of laminar-turbulent transition in Reynolds-averaged Navier-Stokes (RANS) solvers plays a growing role for the computation of complex flows around 3D configurations in aircraft industries. For the flow past transport aircrafts not only the transition from laminar to turbulent flow on wings with high aspect ratio is of importance, but also the transition location on bodies, tailplanes, nacelles, and around intersections of these components has to be known in order to accurately predict the aerodynamic performance.

Generally, boundary layer transition can be caused by different mechanisms. In fully three dimensional boundary layers, there may exist a significant crossflow velocity component that leads to crossflow (CF) instability, whereas in more two dimensional flow regions the flow may be unstable due to Tollmien-Schlichting (TS) waves.

Within the german national project MEGADESIGN, the Institute for Fluid Mechanics at Braunschweig Technical University has developed a transition prediction module for general 3D configurations. This module uses the 3D RANS flow field to determine inviscid streamlines along which the transition criteria are applied. The module provides a wide range of transition criteria including the so called eN-method based on the linear stability theory. The module is embedded in the DLR RANS solver TAU and is fully capable of performing transition prediction for parallel computing.

 

Publications:

[1]

Krimmelbein, N., Radespiel, R., Nebel, C.:
Numerical Aspects of Transition Prediction for Three Dimensional Configurations.
AIAA-2005-4764, 35th AIAA Fluid Dynamics Conference & Exhibit, Toronto, 6-9 June 2005
download (PDF, 1452 KB)

 

[2]

Krimmelbein, N., Radespiel, R.:
Transition prediction for three-dimensional flows using parallel computation.
Comp. Fluids, 2008. doi:10.1016/j.compfluid.2008.01.004
DOI link

 

Figures:

 

Transition line (numerical) and cf-distribution (from experiment) on prolate spheroid


 

 

Inviscid streamlines and transition lines on generic transport aircraft

 

 


  aktualisiert am 05.10.2011
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