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.
*We acknowledge that the results reported in this paper have been achieved using the LEAP project on LEONARDO based at CINECA, Casalecchio di Reno, Italy.Matteo Bernardini has been supported byNext Generation EU, under the Italian PNRR programme, CN1 HPC big data and quantum computing funds.
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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