This project proposes to perform unprecedented direct numerical simulations of subsonic and supersonic turbulent boundary layers over rough walls.
It plans to exploit the computational power of LUMI-G to simulate turbulent flow over rough walls at friction Reynolds number 6000.
This will allow the team to reach the large scale separation encountered in real application. The research will consider Mach numbers of 0.3, 2 and 4, with the main goal to explore the effect of compressibility and to improve the understanding of the flow over thermal protection systems of space vehicles. The project will leverage the high computational efficiency of our compressible flow solver STREAmS to explore Reynolds and Mach number regimes that have not been accessible so far.
The expected outcome is for the dataset generated in this project will represent a breakthrough in the study of turbulent flows over rough walls.