Computational analysis shows a splitter plate reduces separation and flow unsteadiness in supersonic inlets, indicating passive control effectiveness.
A passive control device to mitigate shock-induced separation in a generic supersonic inlet model is computationally studied. The simulations were based on the Favre-averaged Navier–Stokes equations with the Spalart–Allmaras (SA) turbulence model. The shockwave was generated by an 8° turn supersonic inlet. The Mach number in the inlet was varied between 2.1 and 2.46. The baseline shockwave/boundary layer interaction (SBLI) simulation results compare favorably with experimental data. The passive device, in the form of a splitter plate, eliminates both the separation and flow unsteadiness. The splitter plate causes reduction in the total pressure of the boundary layer at the exit of the inlet due to increased skin friction on the floor and due to wake of the plate.
No takes yet. Share an insight, caveat, or question.
Wahidi et al. (2025) studied this question.
Synapse has enriched 4 closely related papers on similar clinical questions. Consider them for comparative context: