Experimental and Numerical Investigation of Transonic Bump Flow
A combined experimental and numerical investigation of transonic shock wave/boundary layer interaction over a wall-mounted bump has been undertaken looking at the details of the flow and the capability of CFD in predicting such complex, yet fundamental, aerodynamic interactions. The transonic wind tunnel of the Queens University of Belfast (QUB) has been employed for experiments that were combined with CFD investigations carried out by the University of Liverpool (ULIV) and the Institut de Méchanique des Fluides de Toulouse (IMFT). Zonal LES methods based on wall modelling, and computations using the Organised Eddy Simulation method were used for the numerical solutions. The shock unsteadiness was not resolved by any of the employed statistical turbulence closures. On the contrary, attempts to use turbulence simulation resulted in unsteady flow solutions. Based on the obtained results, a flow mechanism has been suggested which was found to be in agreement with previous experimental observations. This work was carried out as part of the UFAST F6 EC research project in unsteady shock/boundary-layer interaction.
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