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. The solver models weakly compressible fluid flows over complex three-dimensional bodies based on an immersed boundary method with geometry-based and flow-based automatic mesh adaption. Its high accuracy and unprecedented performance is demonstrated for high Reynolds number aerodynamic benchmark cases and compared to recent results from literature. In addition, the successful validation against experimental data for the Lilium Jet canard is discussed.@en

We scrutinize new and previously published Large Eddy Simulation (LES) data for a sonic jet injected into a supersonic crossflow. Jet and crossflow consist of air, the crossflow Mach number is M∞ = 1:6 and the jet to crossflow momentum ratio is J = 1:7. For this case, experimental measurements and rich numerical data are available in literature. Results of previous numerical studies and our LES are in excellent agreement. However, all numerical data sets show very similar deviations from the available measurements. We analyse sensitivities on uncertain flow parameters to identify the parameters that are most likely responsible for the discrepancy between the numerical and experimental data.@en

A scramjet is an air breathing jet engine for hypersonic flight, in which combustion takes place at supersonic flow velocity. Fast mixing of fuel and the compressed air flow is thus essential for the efficient operation. Because the penetration depth of fuel injection perpendicular to the main flow direction is very small, strut injectors that are positioned directly within the supersonic core flow are usually used in large chambers. We performed large-eddy simulations for a generic strut-injector geometry. The main objective of this paper is the analysis of the pilot injection for flame stabilisation.@en