Aligned with the needs of the aeronautics industry the general aim of the UFAST project is to foster experimental and theoretical work in the highly non-linear area of unsteady shock wave boundary layer interaction (SWBLI). Although in the past several EU projects were aiming at transonic/supersonic flows, the area of unsteady shock wave boundary layer interaction has not yet been treated. Moreover, experimental methods as well as numerical approaches have been improved considerably.
The main study cases, shock waves on wings/profiles, nozzle flows and inlet flows, will serve as a sound basis for open questions posed by the aeronautics industry and can easily be exploited to enable more complex applications to be tackled. In addition to basic flow configurations control methods (synthetic jets, electro-hydrodynamic actuators, stream-wise vortex generators and transpiration flow) will be investigated for controlling both interaction and inherent flow unsteadiness.
The interaction unsteadiness is initiated and/or generated by SWBLI itself but it is often destabilised by the outer flow field. Therefore, the response of shock wave and separation to periodic excitations is of utmost importance and is included in the research program.
Thus emphasis is placed on closely coupled experiments and numerical investigations to allow for feeding back numerical results to the experiments and vice versa for the sake of identifying and overcoming weaknesses in both approaches.
Using RANS/URANS and hybrid RANS-LES methods, UFAST will assess new methods for turbulence modelling in particular for unsteady, shock dominated flow. Moreover, LES methods will be applied to resolve the large coherent structures that govern SWBLI. This way, UFAST will investigate the range of applicability between RANS/URANS and LES.
In order to properly compare experimental and theoretical data, a data base will be created. The UFAST Web site will be used for knowledge dissemination.