Abstract
A simple hybrid difference scheme applicable to shock wave flows is proposed. The scheme remains monotone near shock waves and switches to a low-dissipative nonmonotone difference scheme in smooth flow regions, thus controlling the amount of numerical dissipation. This is achieved by smoothly decreasing a monotonizing correction term down to the prescribed threshold value depending on an indicator of solution smoothness. As an example, the laminar–turbulent transition in a supersonic boundary layer over a flat plate at a Mach number of 3 is simulated. The numerical results are compared with those of other works based on dissipative and low-dissipative schemes. More specifically, we compare the spectral characteristics of disturbances in the linear and nonlinear development domains, the transient flow structure, and averaged boundary layer characteristics.
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Funding
This work was supported by the Russian Science Foundation (project no. 21-19-00307) and was performed at the Moscow Institute of Physics and Technology with the use of computing resources of the federal collective use center Complex for Simulation and Data Processing for Mega-science Facilities at NRC “Kurchatov Institute,” http://ckp.nrcki.ru/.
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Translated by I. Ruzanova
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Egorov, I.V., Nguyen, N.C. Simulation of the Laminar–Turbulent Transition by Applying Hybrid Difference Schemes. Comput. Math. and Math. Phys. 62, 658–673 (2022). https://doi.org/10.1134/S0965542522040054
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DOI: https://doi.org/10.1134/S0965542522040054