Supersonic wall turbulence at high Reynolds numbers
ORAL
Abstract
We perform a Direct Numerical Simulation of supersonic turbulent boundary layer flow up to Reτ=5500, considering a Mach number of 2 and adiabatic wall.
This allows us to approach an asymptotically high–Reynolds number state, capturing flow features that are not visible at lower Reynolds numbers.
In particular, the presence of a true log-layer enables us to assess important aspects such as the outer peak of the velocity variance, scaling of velocity spectra and the intensity of very-large-scale motions.
We expect the present data to highlight the effect of compressibility at high Reynolds numbers by comparing them with recent high Reynolds DNS of low speed flows [Pirozzoli et al., JFM, 2021].
Moreover, the comparison with different flow cases at high Re is relevant in assessing common features, as well as flow specific ones.
This allows us to approach an asymptotically high–Reynolds number state, capturing flow features that are not visible at lower Reynolds numbers.
In particular, the presence of a true log-layer enables us to assess important aspects such as the outer peak of the velocity variance, scaling of velocity spectra and the intensity of very-large-scale motions.
We expect the present data to highlight the effect of compressibility at high Reynolds numbers by comparing them with recent high Reynolds DNS of low speed flows [Pirozzoli et al., JFM, 2021].
Moreover, the comparison with different flow cases at high Re is relevant in assessing common features, as well as flow specific ones.
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Presenters
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Matteo Bernardini
Sapienza University of Rome, Department of Mechanical and Aerospace Engineering, Sapienza University of Rome, Rome, Italy
Authors
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Matteo Bernardini
Sapienza University of Rome, Department of Mechanical and Aerospace Engineering, Sapienza University of Rome, Rome, Italy
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Michele Cogo
Università degli Studi di Padova
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Francesco Picano
University of Padova
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Francesco Salvadore
CINECA