Direct numerical simulation of laminar-turbulent flow over a flat plate at hypersonic flow speeds

被引：33

作者：

Egorov, I. V. ^{[1
,2
]}

Novikov, A. V. ^{[1
,3
]}

机构：

[1] Cent Aerodynam Inst, Ul Zhukovskogo 1, Zhukovskii 140180, Moscow Oblast, Russia

[2] Russian Acad Sci, Inst Analyt Instrumentat, 2 Ya Brestskaya Ul 19-18, Moscow 123056, Russia

[3] Moscow Inst Phys & Technol, Inst Skii Per 9, Dolgoprudnyi 147700, Moscow Oblast, Russia

来源：

COMPUTATIONAL MATHEMATICS AND MATHEMATICAL PHYSICS | 2016年 / 56卷 / 06期

基金：

俄罗斯科学基金会; 俄罗斯基础研究基金会;

关键词：

direct numerical simulation; laminar-turbulent transition; hypersonic flows; boundary layer; ITERATION METHODS; BOUNDARY-LAYERS; SEPARATED FLOW; EQUATIONS; DISTURBANCES; TRANSITION; SCHEMES;

D O I：

10.1134/S0965542516060129

中图分类号：

O29 [应用数学];

学科分类号：

070104 ;

摘要：

A method for direct numerical simulation of a laminar-turbulent flow around bodies at hypersonic flow speeds is proposed. The simulation is performed by solving the full three-dimensional unsteady Navier-Stokes equations. The method of calculation is oriented to application of supercomputers and is based on implicit monotonic approximation schemes and a modified Newton-Raphson method for solving nonlinear difference equations. By this method, the development of three-dimensional perturbations in the boundary layer over a flat plate and in a near-wall flow in a compression corner is studied at the Mach numbers of the free-stream of M = 5.37. In addition to pulsation characteristic, distributions of the mean coefficients of the viscous flow in the transient section of the streamlined surface are obtained, which enables one to determine the beginning of the laminar-turbulent transition and estimate the characteristics of the turbulent flow in the boundary layer.

引用

页码：1048 / 1064

页数：17

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