The accurate simulation of separated flows induced by impinging shock waves is an argument of great interest for the aeronautical and aerospace industry.
Shock boundary layer interactions represent a critical fluid flow phenomenon that must be accurately considered to improve the airplane performance in terms of both fuel consumption and emissions.
With this proposal we aim to generate a highly resolved turbulence statistics dataset for a transonic flow configuration to be used for improving RANS and LES wall modelling. Enhancing the model reliability will contribute to significant improvements in design and reduction of costs and emission.
The particular test case considered is the axisymmetric transonic hump experiment, a new configuration of the Bachalo-Johnson test case.
The experiment consists of an axisymmetric bump on a cylinder aligned with the wind tunnel to produce a shock wave inducing the separation of the turbulent boundary layer. This proposal is strictly related to the HiFi-TURB EU-H2020 (2019-2022, G.A. 814837, https://cordis.europa.eu/project/id/814837) focused on the development of innovative turbulence models for complex aerodynamic flows. The HiFi-TURB project aims at using high-fidelity LES and DNS data and artificial intelligence for the improvement of turbulence models.
University of Bergamo is part of the consortium and contributes to HiFi-TURB in generating detailed LES/DNS datasets using the high-order Discontinuous Galerkin code MIGALE.