Assessment of Reynolds number effects in supersonic turbulent boundary layers
L. Laguarda, S. Hickel, F.F.J. Schrijer, B.W. van Oudheusden (2024)
International Journal of Heat and Fluid Flow 105: 109234. doi: 10.1016/j.ijheatfluidflow.2023.109234
Wall-resolved large-eddy simulations (LES) are performed to investigate Reynolds number effects in supersonic turbulent boundary layers (TBLs) at Mach 2.0. The resulting database covers more than a decade of friction Reynolds number Reτ from 242 to 5554, which considerably extends the parameter range of current high-fidelity numerical studies. Reynolds number trends are identified on a variety of statistics for skin-friction, velocity and thermodynamic variables. The efficacy of recent scaling laws as well as compressibility effects are also assessed.
GPU-accelerated simulations for eVTOL aerodynamic analysis
V. Pasquariello, Y. Bunk, S. Eberhardt, P.-H. Huang, J. Matheis, M. Ugolotti, S. Hickel (2023)
AIAA paper 2023-2107. doi: 10.2514/6.2023-2107
The demand for fast, high-fidelity, scale-resolving computational fluid dynamics (CFD) simulations is continuously growing. Especially new emerging aviation technologies, such as electrical vertical take-off and landing aircraft (eVTOL), strongly rely on advanced numerical methods to retain development life-cycle costs and achieving design targets more quickly. This paper presents a cutting-edge large-eddy simulations (LES) solver developed to enable over-night turnaround times for full aircraft simulations on advanced graphics processing unit (GPU) architectures.
Wall modeled large-eddy simulation of the VFE-2 delta wing
C. Zwerger, S. Hickel, C. Breitsamter, N.A. Adams (2015)
AIAA paper 2015-2572. doi: 10.2514/6.2015-2572
We performed wall-modeled large-eddy simulation of the flow field around the VFE-2 delta wing, focusing on two aspects: (1) leading-edge bluntness effects on the primary vortex separation and (2) vortex breakdown above the wing and its control. Regarding aspect (1), the VFE-2 delta wing with sharp leading-edge (SLE) and medium radius round leading-edge (MRLE) are considered for three angles of attack α = {13°, 18°, 23°} leading to different overall flow characteristics.
Wall-modelled Implicit Large-Eddy Simulation of the RA16SC1 Highlift Configuration
M. Meyer, S. Hickel, C. Breitsamter, N.A. Adams (2013)
AIAA paper 2013-3037. doi: 10.2514/6.2013-3037
Industrially applied Computational Fluid Dynamics still faces a challenge when it comes to the accurate prediction of the complex flow over realistic highlift configurations. In this paper we demonstrate that the flow over the 3-element RA16SC1 highlift configuration can be efficiently and accurately predicted with Implicit Large-Eddy Simulation (ILES) on Cartesian adaptive grids.
A parametrized non-equilibrium wall-model for large-eddy simulations
S. Hickel, E. Touber, J. Bodart, J. Larsson (2012)
Proceedings of the 2012 Summer Program, Center for Turbulence Research, Stanford University.
Wall-models are essential for enabling large-eddy simulations of realistic problems at high Reynolds numbers. The present study is focused on approaches that directly model the wall shear stress, specifically on filling the gap between models based on wall-normal ordinary differential equations (ODEs) that assume equilibrium and models based on full partial differential equations that do not. We develop ideas for how to incorporate non-equilibrium effects (most importantly, strong pressure-gradient effects) in the wall- model while still solving only wall-normal ODEs.
Wall modeling for implicit large-eddy simulation and immersed-interface methods
Z.L. Chen, S. Hickel, A. Devesa, J. Berland, N.A. Adams (2013)
Theoretical and Computational Fluid Dynamics 28: 1-21. doi: 10.1007/s00162-012-0286-6
We propose and analyze a wall model based on the turbulent boundary layer equations (TBLE) for implicit large-eddy simulation (LES) of high Reynolds number wall-bounded flows in conjunction with a conservative immersed-interface method for mapping complex boundaries onto Cartesian meshes. Both implicit subgrid-scale model and immersed-interface treatment of boundaries offer high computational efficiency for complex flow configurations.