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Direct Numerical Simulation on Mach Number and Wall Temperature Effects in the Turbulent Flows of Flat-Plate Boundary Layer

Published online by Cambridge University Press:  28 November 2014

Xian Liang  and
Xinliang Li
Xian Liang
Affiliation:
School of Mathematics and Information Science, Beifang University for Nationalities, Yinchuan 750021, China
Xinliang Li*
Affiliation:
LHD, Institute of Mechanics, Chinese Academy of Sciences, No. 15 Beisihuanxi Road, Beijing 100190, China
*
*Email addresses:liangxian@imech.ac.cn(X. Liang), lixl@imech.ac.cn(X. L. Li)
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Abstract

In this paper, direct numerical simulation (DNS) is presented for spatially evolving turbulent boundary layer over an isothermal flat-plate at Ma∞ = 2.25,5,6,8. When Ma∞ = 8, two cases with the ratio of wall-to-reference temperature Tω/T∞ = 1.9 and 10.03 are considered respectively. The wall temperature approaches recovery temperatures for other cases. The characteristics of compressible turbulent boundary layer (CTBL) affected by freestream Mach number and wall temperature are investigated. It focuses on assessing compressibility effects and the validity of Morkovin's hypothesis through computing and analyzing the mean velocity profile, turbulent intensity, the strong Reynolds analogy (SRA) and possibility density function of dilatation term. The results show that, when the wall temperature approaches recovery temperature, the effects of Mach number on compressibility is insignificant. As a result, the compressibility effect is very weak and the Morkovin's hypothesis is still valid for Mach number even up to 8. However, when Mach number equal to 8, the wall temperature effect on the compressibility is sensitive. In this case, when Tω/T∞ = 1.9, the Morkovin's hypothesis is not fully valid. The validity of classical SRA depends on wall temperature directly. A new modified SRA is proposed to eliminate such negative factor in near wall region. Finally the effects of Mach number and wall temperature on streaks are also studied.

Keywords

47.27.E-47.27.nb47.40.KiHypersonicdirectly numerical simulationcompressibility effectsturbulent boundary layerstrong Reynolds analogy
Type
Research Article
Information
Communications in Computational Physics , Volume 17 , Issue 1 , January 2015 , pp. 189 - 212
Copyright
Copyright © Global Science Press Limited 2015 

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