Landmark Direct Numerical Simulations of Separation and Transition for Aerospace-Relevant Wall-Bounded Shear Flows
Principal Investigator: Hermann Fasel, University of Arizona
Affiliation: University of Arizona
Proposal Title: “Landmark Direct Numerical Simulations of Separation and Transition for Aerospace-Relevant Wall-Bounded Shear Flows”
Machine: Cray X1E
Allocation: 400,000 processor hours
Research Summary: This project is conducting landmark direct numerical simulations of flow problems important to the development of modern airplane wings and new jet engines that incorporate active flow control (AFC) technology. The physics of transition and separation on the upper surfaces of aircraft wings (external flow) and low-pressure turbine blades (internal flow) will be investigated, as will the use of AFC (e.g. pulsed vortex generator jets, or plasma actuators) for separation control. The project team is also working to explain the dynamics of coherent structures in Coanda flows, which is crucial for the development of effective and efficient Coanda flow devices.