Transition Prediction for 3D Flows Using a Reynolds-Averaged Navier-Stokes Code and N-Factor Methods

Nebel, Christoph; Radespiel, Rolf; Wolf, Torsten

doi:10.2514/6.2003-3593

Cited by 24 publications

(24 citation statements)

References 4 publications

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“…The accuracy of the predicted transition has been improved compared to earlier attempts 4 . The improvement was mainly achieved by the replacement of the database methods with the stability code COAST3.…”

Section: Discussionmentioning

confidence: 85%

“…By using the inviscid streamline assumption a simple way is found to determine transition locations with the e N -method in three dimensional flow. According to experiences with infinite swept wings, the difference between the inviscid flow direction and the direction of the group velocity is only a few degrees 2,4,10 . Hence, the transition module is used to calculate inviscid streamlines, extract the boundary layer data and velocity profiles from these streamlines and provide the data as input for the stability solver COAST3.…”

Section: B Transition Prediction Methodsmentioning

confidence: 99%

“…Both, crossflow and Tollmien-Schlichting instabilities can be described by the e N -method 2 . At the Institute for Fluid Mechanics at Braunschweig Technical University a transition prediction module was previously integrated into the Reynolds-averaged Navier-Stokes code TAU 3,4 . This module uses the 3D RANS flow field to define integration paths for the calculation of the N-factor and takes the RANS boundary layer data as mean flow for the stability analysis.…”

Section: Introductionmentioning

confidence: 99%

“…Crossflow and Tollmien-Schlichting instabilities are analyzed with database methods of Casalis and Arnal 5 and Stock and Degenhart 6 respectively. The module is capable of predicting transition in 2D and 2.5D flows on airfoils and infinite swept wings and on simple geometries for 3D flows 4 . This module has been used as a base to develop an enhanced version for the analysis of flows past more complex configurations.…”

Section: Introductionmentioning

confidence: 99%

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Numerical Aspects of Transition Prediction for Three-Dimensional Configurations

Krimmelbein

Radespiel

Nebel³

2005

35th AIAA Fluid Dynamics Conference and Exhibit

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The feasibility to predict transition for three dimensional configurations is presented by means of a coupled program system consisting of a 3D Navier-Stokes solver, a transition module and a stability code. The assumption to use inviscid streamlines as integration paths for the N-factor calculation makes it possible to use linear stability theory in a straightforward way for three dimensional flows. The developed transition module has been adapted to be used with sequential and parallel computations to account for the increased computational demand for three dimensional configurations. Detailed investigations have been carried out, to show the ability of the Navier-Stokes code to provide data of three dimensional boundary layers of high accuracy needed for the stability analyses. Applications of the transition prediction method using the 2N-factor method for the case of an inclined prolate spheroid shows reasonably good results compared to experiments. First application of the transition prediction tool on a generic transport aircraft show promising results for the ability to predict transition on complex geometries.

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Section: Discussionmentioning

confidence: 85%

Section: B Transition Prediction Methodsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Numerical Aspects of Transition Prediction for Three-Dimensional Configurations

Krimmelbein

Radespiel

Nebel³

2005

35th AIAA Fluid Dynamics Conference and Exhibit

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“…The unstructured/hybrid RANS solver TAU, [14], [4] and [15], has been provided with a general transition prediction functionality which can be applied to general three-dimensional aircraft configurations. The developments and first technical validation steps were carried out at the Institute of Fluid Mechanics (ISM) of the University of Braunschweig, [10], [2] and [3]. The code can be used together with a laminar boundary-layer method, [1], for the calculation of highly accurate laminar boundary-layer data.…”

Section: Introductionmentioning

confidence: 99%

Automatic Transition Prediction for Three-Dimensional Aircraft Configurations Using the DLR TAU Code

Krumbein¹,

Krimmelbein²,

Schrauf

2010

Notes on Numerical Fluid Mechanics and Multidisciplinary Design

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SummaryA Reynolds-averaged Navier-Stokes solver, a laminar boundary-layer code and a fully automated local, linear stability code for the prediction of TollmienSchlichting and cross flow instabilities were coupled for the automatic prediction of laminar-turbulent transition on general aircraft configurations during the ongoing flow computation. The procedure is applied to different threedimensional wing-body configurations and the sensitivity of the coupled system to a variety of coupling parameters is investigated.

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Navier-Stokes Airfoil Computations with Automatic Transition Prediction using the DLR TAU Code - A Sensitivity Study

Krumbein

2006

New Results in Numerical and Experimental Fluid Mechanics V

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The hybrid DLR RANS solver TAU coupled to a transition prediction module was successfully applied to a single-element airfoil automatically taking into account the locations of laminar-turbulent transition. The experimentally measured transition locations could be reproduced with very high accuracy. A sensitivity study of the parameters of the coupling procedure was performed in order to investigate the behaviour of the coupled system with respect to the accuracy and robustness of the iteration procedure for the transition locations. The transition prediction coupling structure and the underlying algorithm are described. The functions of the coupling parameters and their impact on the transition location iteration and the convergence of the simulations are described and documented.

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Transition Prediction for 3D Flows Using a Reynolds-Averaged Navier-Stokes Code and N-Factor Methods

Cited by 24 publications

References 4 publications

Numerical Aspects of Transition Prediction for Three-Dimensional Configurations

Numerical Aspects of Transition Prediction for Three-Dimensional Configurations

Automatic Transition Prediction for Three-Dimensional Aircraft Configurations Using the DLR TAU Code

Navier-Stokes Airfoil Computations with Automatic Transition Prediction using the DLR TAU Code - A Sensitivity Study

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