Direct Numerical Simulation of Swept-Wing Laminar Flow Control Using Pinpoint Suction

被引：1
|
作者：
Friederich, Tillmann A. [1 ]
Kloker, Markus J. [1 ]
机构：
[1] Univ Stuttgart, Inst Aerodynam & Gasdynam, D-70550 Stuttgart, Germany
来源：
HIGH PERFORMANCE COMPUTING IN SCIENCE AND ENGINEERING '10 | 2011年
关键词：
3-DIMENSIONAL BOUNDARY-LAYER; SECONDARY INSTABILITY; TRANSITION MECHANISMS; VORTICES;
D O I：
10.1007/978-3-642-15748-6_18
中图分类号：
TP39 [计算机的应用];
学科分类号：
081203 ; 0835 ;
摘要：
Recent investigations of laminar flow control for swept-wing boundary-layer flows provide promising results with respect to crossflow-transition delay using a technique called pinpoint suction. Strong, localized suction through holes accurately positioned with respect to the crossflow-vortex position can directly weaken the growth of secondary instabilities that are responsible for the final laminar breakdown. With our incompressible code N3D extremely resolved grids in wall-normal direction have to be used to obtain numerical convergence. In order to confirm the results with such strong, localized suction, a single suction hole has been simulated in a Blasius boundary layer with the N3D code and additionally with our compressible code NS3D. Results from grid studies carried out for both codes as well as a comparison of the compressible/incompressible results are provided. Incompressible simulations with various pinpoint suction scenarios in the swept-wing flow show the application of successful pinpoint suction. Performance data for both codes focusing on a comparison of the NEC SX-8/SX-9 conclude this report.
引用
收藏
页码：231 / 250
页数：20
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