Shock-Induced Corner Separation in Supersonic Duct Flows
The effect of wall separation control on multiple walls was investigated. This study used injection-assisted micro-vortex generators (MVGIs) in a duct flow. Three cases, namely, no control (case A), three-wall control (case B), and four-wall control (case C), were investigated using schlieren imaging, oil flow visualization, and wall pressure measurements. The various shock/compression waves from all the MVGIs were found to interact ahead of the normal shock. Oil flow visualizations on the bottom wall show that there are notable variations in center and corner separations when more walls are being controlled. Pressure recovery for three walls having control was higher than that for no control case, and the recovery for four-wall control case was much higher than that of three-wall control case. The separation zone sizes and the pressure recovery suggest that there is interaction between the separation zones in a duct at a cross section.
- 5.S. Vaisakh, T.M. Muruganandam, Control of boundary layer separation in supersonic flow using injection through micro ramps, in 30th International Symposium on Shock Waves, July 19–24, Israel, 2015Google Scholar