Unsteady flow with separation behind a shock wave diffracting over curved walls

Abstract

The unsteady separation of the compressible flow field behind a diffracting shock wave was investigated along convex curved walls, using shock tube experimentation at large length and time scales, complemented by numerical computation. Tests were conducted at incident shock Mach numbers of \(M_{\hbox {s}} =\) 1.5 and 1.6 over a 100 mm radius wall over a dimensionless time range up to \(\tau \le \) 6.45. The development of the near wall flow at \(M_{\hbox {s}} =\) 1.5 has been described in detail and is very similar to that observed for slightly lower \(\tau \)’s at \(M_{\hbox {s}} =\) 1.6. Computations were performed at wall radii of 100 and 200 mm and for incident shock Mach numbers from 1.5 up to and including Mach 2.0. Comparing dimensionless times for different size walls shows that for a given value of \(\tau \) the flow field is very similar for the various wall radii published to date and tested in this study. Previously published results that were examined alongside the results from this study had typical values of \(1.6 < \tau < 3.2\). At the later times presented here, flow features were observed that previously had only been observed at higher Mach numbers. The larger length scales allowed for a degree of Reynolds number independence in the results published here. The effect of turbulence on the numerical and experimental results could not be adequately examined due to limitations of the flow imaging system used and a number of questions remain unanswered.