Numerical and Experimental Examination of Shock Control Bump Flow Physics

Vortical Structures on Three-Dimensional Shock Control Bumps

“…This was chosen as separated flows are typically poorly modelled by RANS simulations and this therefore represents a 'di cult' test case for the CFD. Results of this study, in the form of profiles of c p and C f , are shown in figure 7, adapted from [16,26]. Level 3 fails to resolve the shock signature and completely misses the separation, whilst level 2 broadly captures the shock structure but C f does not get su ciently low to suggest incipient separation.…”

“…In order to find an appropriate balance between computational cost and solution accuracy, a grid .03c mesh refinement Figure 6: Details of the mesh used for computations convergence study was performed, as first described in [16,26]. This examined a dense reference ("level 0") mesh consisting of 46 million cells, as well as three levels of coarsening: level 1 with 5.8 million cells; level 2 with 0.75 million; and level 3 with 0.1 million.…”

“…They are placed symmetrically on the centreline of the domain, so that the e↵ective geometry is an infinite array of uniformly spaced bumps on the unswept wing. Figure 7: Results of the grid convergence study, adapted from [16,26] The flight conditions used are shown in table 2, which were chosen by [16] shown in figure 9. The HSCB is a smooth contour bump originally defined by König et al, [8], the profiles of which are given by formulae for the bending of an elastic beam under a point load with di↵erent end conditions: the longitudinal profile has a 'simply supported' end at the bump nose and a clamped end at the bump trailing edge; the lateral profile is simply supported on both sides.…”