Journal
AEROSPACE SCIENCE AND TECHNOLOGY
Volume 86, Issue -, Pages 487-496Publisher
ELSEVIER FRANCE-EDITIONS SCIENTIFIQUES MEDICALES ELSEVIER
DOI: 10.1016/j.ast.2019.01.036
Keywords
Boundary layer transition; Laminar fluctuation kinetic energy; Intermittency; Natural transition; Laminar separation bubble induced transition; Crossflow instabilities
Categories
Funding
- International Postdoctoral Exchange Fellowship Program [20180018]
- National Science Foundation for Young Scholars [11602199, 11802245]
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Because of the great influence of transition phenomena in aerodynamic property calculations, boundary layer transition has always been a hot research topic in the past few decades. Meanwhile, the prediction methods for boundary layer transition need to be established, researched and enhanced. In order to build a computational fluid dynamics (CFD) compatible transition model, the authors propose a two-equation transport transition model in this paper considering analysis results through linear stability theory (LST). This new transition model consists of one transport equation for laminar fluctuation kinetic energy and another for intermittency factor. Without boundary layer integration and other nonlocal operations, all the variables in this new transition model can be calculated locally so that present model is compatible with CFD parallel computation. Laminar separation bubble induced transition, Tollmien-Schlichting (T-S) instabilities and stationary crossflow instabilities (CF) dominated transition are modeled in the transport equation. The validation tests have been conducted on the classical Schubauer & Klebanoff flat plate, natural laminar airfoil NLF(1)-0416, NLF(2)-0415 infinite swept wing, classical sickle swept wing and 6:1 inclined prolate spheroid using this fully-local transition model. Since all the test cases are in accord with experimental data, the present transition model could be widely applied to aeronautical flows in low-disturbance environment. (C) 2019 Elsevier Masson SAS. All rights reserved.
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