Slide 1 > 24 th Applied Aerodynamics Conference > A. Krumbein Hyatt Regency, San Francisco, California > 06-June-06 Automatic Transition Prediction and Application to 3D High-Lift Configurations Andreas Krumbein German Aerospace Center - DLR Institute of Aerodynamics and Flow Technology, Numerical Methods
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Hyatt Regency, San Francisco, California > 06-June-06 Slide 1 > 24 th Applied Aerodynamics Conference > A. Krumbein Automatic Transition Prediction and.
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Slide 1 > 24th Applied Aerodynamics Conference > A. KrumbeinHyatt Regency, San Francisco, California > 06-June-06
Automatic Transition Prediction and Application to 3D High-Lift Configurations
Andreas KrumbeinGerman Aerospace Center - DLRInstitute of Aerodynamics and Flow Technology, Numerical Methods
Slide 2 > 24th Applied Aerodynamics Conference > A. KrumbeinHyatt Regency, San Francisco, California > 06-June-06
Outline
Outline
Slide 3 > 24th Applied Aerodynamics Conference > A. KrumbeinHyatt Regency, San Francisco, California > 06-June-06
Introduction
Introduction
Aircraft industry requirements:
RANS based CFD tool with transition prediction
Automatic, no intervention of the user
Reduction of modeling based uncertainties
Accuracy of results from fully turbulent flow or flow with prescribed transition often not satisfactory
Improved simulation of the interaction between transition locations and separation
Slide 4 > 24th Applied Aerodynamics Conference > A. KrumbeinHyatt Regency, San Francisco, California > 06-June-06
Slide 20 > 24th Applied Aerodynamics Conference > A. KrumbeinHyatt Regency, San Francisco, California > 06-June-06
Conclusion
Conclusion The complete coupled system (RANS solver & transition prediction module) was succesfully applied to a complex aircraft configuration of industrial relevance WB with 3-element high-lift system
The predicted transition lines are reasonable and quite different from estimated ones based on an experiment
But, they are of preliminary character:Transition prediction module does not yet cover all transition mechanisms which can occur in 3d high-lift flows
Transition inside laminar separation bubbles, attachment line transition & by-pass trasition can not be detected
More validation on complex configurations necessary
It seems to be evident that transition inside laminar separation bubbles is of high importance
It was shown that a fully turbulent simulation or an estimation of the transition lines can result in significant deficiencies
Slide 21 > 24th Applied Aerodynamics Conference > A. KrumbeinHyatt Regency, San Francisco, California > 06-June-06
Further comparisons for the current tast cases:Skin friction lines vs. flow visualizations
Global coeffcients: lift & drag
More validation cases, e.g. DLR F5 wing → transonic test case & other more complex test cases