Summary
Shock/boundary layer interaction at transonic flow conditions had been the investigated using wind tunnel experimentation and computational fluid dynamics. The main objective of the investigation was to establish a database of measurements to use for CFD validation and, subsequently, exploit the CFD to extract further understanding about the flow mechanism and physics. Of particular interest was the unsteady transonic interaction at conditions approaching aircraft flight. At first, a detailed study of the effect of the perforated and solid walls on the obtained shock configuration was carried out using the URANS approach. This resulted in a decision to adopt a configuration with a solid contoured upper wall. At the same time, issues related to the air humidity in the tunnel were investigated by QUB to ensure that comparisons against the clean air computations of ULIV were possible. Following this, computations with URANS and zonal LES based on wallfunctions were undertaken to resolve the flow along with Organised Eddy Simulations (OES). For this test case, there was no low-frequency unsteadiness as initially expected. Instead a rapid small-amplitude shock excursion was observed. URANS was not able to resolve this phenomenon and the employed turbulence simulation methods had moderate success as well. The experiments were conducted at the Queens University of Belfast (QUB) with simulations carried out by the Institut de Méchanique des Fluides de Toulouse (IMFT) and the University of Liverpool (ULIV).
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Doerffer, P., Hirsch, C., Dussauge, JP., Babinsky, H., Barakos, G.N. (2010). Bump at a Wall (George Barakos). In: Unsteady Effects of Shock Wave Induced Separation. Notes on Numerical Fluid Mechanics and Multidisciplinary Design, vol 114. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-642-03004-8_2
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