A transition prediction method for flow over airfoils based on high-order dynamic mode decomposition-Reference-Cited by-同舟云学术

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A transition prediction method for flow over airfoils based on high-order dynamic mode decomposition

Published:2019-11 Issue:11 Volume:32 Page:2408-2421
ISSN:1000-9361
Container-title:Chinese Journal of Aeronautics
language:en
Short-container-title:Chinese Journal of Aeronautics

Author:

WU Mengmeng,HAN Zhonghua,NIE Han,SONG Wenping,CLAINCHE Soledad Le,FERRER Esteban

Funder

National Natural Science Foundation of China

Aeronautical Science Foundation of China

Publisher

Elsevier BV

Subject

Mechanical Engineering,Aerospace Engineering

Reference47 articles.

1. Fasel HF, Meitz HL, Bachman CR. DNS and LES for investigating transition and transition control. Reston: AIAA; 1997. Report No.: AIAA-1997-1820.

2. Schlatter P, Örlü R. Assessment of direct numerical simulation data of turbulent boundary layers. J Fluid Mech 2010; 659:116–26.

3. Muppidi S, Mahesh K. DNS of transition in supersonic boundary layers. Reston: AIAA; 2010. Report No.: AIAA-2010-4440.

4. Smith AMO, Gamberoni N. Transition, pressure gradient and stability theory. Berkeley: Douglas Aircraft Division; 1956. Report No.: ES 26388.

5. Van Ingen JL. The eN method for transition prediction. Historical review of work at TU Delft. Reston: AIAA; 2008. Report No.: AIAA-2008-3830.

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