High-Reynolds number effects in shock-wave/turbulent boundary-layer interactions

Conference paper (2022)

Authors

L. Laguarda Aerodynamics - Aerospace Engineering
S. Hickel Aerodynamics - Aerospace Engineering
F.F.J. Schrijer Aerodynamics - Aerospace Engineering
B.W. van Oudheusden Aerodynamics - Aerospace Engineering
Research Group
Aerodynamics (Aerospace Engineering) (TU Delft)
Copyright: © 2022 L. Laguarda, S. Hickel, F.F.J. Schrijer, B.W. van Oudheusden
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Published Date

2022

Language

English

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Faculty

Aerospace Engineering

Department

Flow Physics and Technology

Research Group

Aerodynamics

Abstract

We investigate Reynolds number effects in shockwave/turbulent boundary-layer interactions (STBLI) with strong mean flow separation. Three wall-resolved large-eddy simulations (LES) are performed for this purpose, with different Reynolds number but otherwise equal flow parameters and simulation setup. The resulting LES data covers more than a decade of friction Reynolds number. The high-Reynolds case, with friction Reynolds number Reτ = 5118 and momentum Reynolds number Reθ = 26438 at the virtual impingement point without the shock, features a turbulent boundary layer with clear inner and outer scale separation. All STBLI simulations exhibit substantial flow reversal and have been integrated for a very long time (90 flow-through times of the full domain length) to properly resolve low-frequency dynamics. Instantaneous and mean flow as well as spectral features are described in detail, together with a modal analysis of the three-dimensional streamwise velocity, streamwise vorticity and pressure fields.

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