Numerical methods for direct numerical simulation (DNS) of complex flow fields including shocks require a robust shock capturing feature, as well as minimal dissipation and dispersion errors to resolve small scales of turbulent fluctuations. DNS-SWL solvers based on high-order Flux Corrected Transport (FCT) scheme and optimized high-order Weighted Essentially Non-Oscillatory (WENO) finite difference schemes enable to reproduce well vortical structures in the boundary and shear layers and highly unsteady dynamics of shock waves for various compressible flows at large Mach and Reynolds numbers range. DNS of three dimensional flows were performed using MPI parallelization on a JUQUEEN Supercomputer.

    Numerical simulations of transonic airfoil flows with pressure waves/shock and shock/boundary layer interactions using optimized high-order WENO finite difference schemes will be presented. The numerical results of the instantaneous three-dimensional transonic flow around the BAC3-11 airfoil show a good agreement with experimental data.

    Coaxial jets with and without a supersonic core flow show a lot of unsteady phenomena such as shear layer instability and transition to turbulence. Their accurate numerical simulation is still challenging despite todays available computing resources. The strategy of using high-fidelity numerical methods and a high spatial resolution helps to increase the range of resolved scales of the flow. This presentation focuses on the numerical simulation of coaxial jets entering into a hot environment. Based on these results a new correlation model and optimisation criteria is proposed to predict the potential core- and supersonic length of the coaxial jet and leading to a significantly increased jet length. In particular, the enlarged supersonic jet length is of interest for special industrial applications.

    Compression ramp flow has been the subject of intensive numerical and experimental investigations at the Shock Wave Laboratory (SWL) since many years. The main goal of this presentation is to study the hypersonic flow over compression ramps with different geometric configurations and conditions using direct numerical simulation. The results clearly show the development and the detailed structure of Görtler vortices downstream of the reattachment region.

Dipl.-Ing. 1984 State Technical University, Izhevsk, Russia, Faculty of Mechanical Engineering

Dr.rer.nat. 1989 Russian Academy of Sciences, Institute of Mathematics, and Mechanics, Izhevsk, Russia

Dr.rer.nat.habil. 1998 Russian Academy of Sciences, Institute of Applied,Mechanics, Izhevsk, Russia

Professor 1998 State Technical University, Izhevsk, Russia

1984 - 1988 Scientific researcher, State Technical University, Izhevsk, Russia,Numerical simulation of rocket engine internal flows

1988 - 1991 Head scientific researcher, Russian Academy of Sciences, Institute of Mathematics and Mechanics, Izevsk, Russia

1991 - 1999 Professor, Head of Physical Flow Mechanics Laboratory, Russian Academy of Sciences, Institute of Applied Mechanics, Izhevsk, Russia

1999 - 2006 Scientific researcher, Mechanics Department, RWTH Aachen University, Germany

2006 - Head of Section Numerical Simulation, Shock Wave Laboratory, RWTH Aachen University, Germany

Membership AIAA, GAMM, MAA

Reviewer Journal of Fluid Mechanics, Computers and Fluids

Direct numerical simulation, Numerical methods,

Turbulent flows, Compressible flows, Shock waves

Direct numerical simulation of transonic airfoil flows,

Wave phenomena at airfoils, Direct numerical simulation of

transitional and turbulent flows, High-order shock-capturing

numerical schemes, Numerical simulation of supersonic and

hypersonic flows, Numerical simulation of detonation waves,

Shock / boundary