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Unsteady effects in shock wave induced separation

Final Report Summary - UFAST (Unsteady effects in shock wave induced separation)

Aligned with the needs of the aeronautics industry, the general aim of the UFAST project was to foster experimental and theoretical work in the highly non-linear area of unsteady shock wave boundary layer interaction (SWBLI). Although previous EU projects concentrated on transonic/supersonic flows, they did not examine unsteady shock wave boundary layer interaction. Important developments in experimental and numerical methods in recent years have now made such research possible.

The main cases of study, shock waves on wings/profiles, nozzle flows and inlet flows, provide 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) have 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/downstream flow field. Therefore, the response of shock wave and separation to periodic excitations is of utmost importance and has been included in the research program.

Thus emphasis is focused on closely linked experiments and numerical investigations to allow the application of numerical results in the experiments and vice versa for the sake of identifying and overcoming weaknesses in both approaches.

The UFAST project has improved knowledge and expertise by delivering:

- reference experiments focused on unsteady effects
- improvement of existing numerical modelling methods
- enhanced understanding of complicated physical phenomena.

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