Abstract
The three-dimensional single-fin configuration finds application in an intake geometry where the cowl-shock wave interacts with the side-wall boundary layer. Accurate numerical simulation of such three-dimensional shock/turbulent boundary-layer interaction flows, which are characterized by the appearance of strong crossflow separation, is a challenging task. Reynolds-averaged Navier–Stokes computations using the shock-unsteadiness modified Spalart–Allmaras model is carried out at Mach of 5 at large fin angle of $$23^{\circ }$$ . The computed results using the modified model are compared to the standard Spalart–Allmaras model and validated against the experimental data. The focus of the work is to implement the modified model and to study the flow physics in detail in the complex region of swept-shock-wave turbulent boundary-layer interaction in terms of the shock structure, expansion fan, shear layer and the surface streamlines. The flow structure is correlated with the wall pressure and skin friction in detail. It is observed that the standard model predicts an initial pressure location downstream of the experiments. The modified model reduces the eddy viscosity at the shock and predicts close to the experiments. Overall, the surface pressure using modified model has predicted accurately at all the locations. The skin friction is under-predicted by both the models in the reattachment region and is attributed to the poor performance of turbulence models due to flow laminarization.
Highlights
The most fundamental three-dimensional shock/boundary-layer interaction is generated on a single fin configuration
Practical applications of single fin configuration include scramjet inlets, where the oblique shock generated by the cowl interacts with the side wall boundary layer
The shock-unsteadiness modified Spalart-Allmaras model and its standard version are used in the computations
Summary
The most fundamental three-dimensional shock/boundary-layer interaction is generated on a single fin configuration. The oblique shock wave generated by the fin interacts with the turbulent boundary layer on the plate and results in flow separation. The single fin shock boundary-layer interaction flows are characterized by localized regions of increased pressure, skin friction and heat transfer rate. Prediction of these surface properties is important in the design of scramjet inlets. Computational fluid dynamic approach is a useful tool to understand the complex three-dimensional flow pattern in these shock-wave/boundary-layer interactions and to predict its influence on the wall data. The computed wall pressure and skin friction using modified model [16] and the standard model [18] is compared with the experimental results [19]
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