Pasha, A.A. Three-Dimensional Modeling Shock-Wave Interaction with a Fin at Mach 5. Arab J Sci Eng (2018). https://doi.org/10.1007/s13369-018-3210-6
Pasha, A.A. Three-Dimensional Modeling Shock-Wave Interaction with a Fin at Mach 5. Arab J Sci Eng (2018). https://doi.org/10.1007/s13369-018-3210-6
Pasha, A.A. Three-Dimensional Modeling Shock-Wave Interaction with a Fin at Mach 5. Arab J Sci Eng (2018). https://doi.org/10.1007/s13369-018-3210-6
Pasha, A.A. Three-Dimensional Modeling Shock-Wave Interaction with a Fin at Mach 5. Arab J Sci Eng (2018). https://doi.org/10.1007/s13369-018-3210-6
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◦. The computed results using the modified model are compared to the standard Spalart-Allmaras model and validated against the experimental data. The focus of 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 to 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 is 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.
Keywords
high speed flows; shock wave; turbulent boundary layer; shock-unsteadiness; separation bubble; turbulence modeling; single fin
Subject
Engineering, Mechanical Engineering
Copyright:
This is an open access article distributed under the Creative Commons Attribution License which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.
