Direct Numerical Simulations of Compressible Turbulent Boundary Layers

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Image: IAG, University of Stuttgart

This project explores laminar-turbulent transition, turbulence, and flow control in boundary layers at various flow speeds from the subsonic to the hypersonic regime. The physical problems under investigation deal with prediction of laminar-turbulent transition on airfoils for aircraft, prediction of critical roughness heights in laminar boundary layers, turbulent drag reduction, the origins of turbulent superstructures in turbulent flows, the use of roughness patterns for flow control, effusion cooling in laminar and turbulent supersonic boundary-layer flow, DNS of disturbance receptivity on a swept wing at high Reynolds numbers, and plasma actuator design for active control of disturbances in a swept-wing flow.

Read the complete user research report at the Gauss Centre for Supercomputing.

Principal Investigators

Ulrich Rist, Markus Kloker, Christoph Wenzel

Institute of Aerodynamics and Gas Dynamics, University of Stuttgart