Navier-Stokes high-lift airfoil computations with automatic transition prediction using the DLR TAU code

被引：0
|
作者：
Krumbein, A. [1 ]
Krimmelbein, N. [2 ]
机构：
[1] Deutsches Zentrum Lift & Raumfahrt eV, AS NV, Bunsenstr 10, D-37073 Gottingen, Germany
[2] Tech Univ Carolo Wilhelmina Braunschweig, ISM, D-38106 Braunschweig, Germany
来源：
NEW RESULTS IN NUMERICAL AND EXPERIMENTAL FLUID MECHANICS VI | 2007年 / 96卷
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D O I：
暂无
中图分类号：
V [航空、航天];
学科分类号：
08 ; 0825 ;
摘要：
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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页码：210 / +
页数：2
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