Abstract
An experimental study has been conducted to examine the interaction of compressible flow structures such as shocks and vortices with a two-dimensional ejector geometry using a shock-tube facility. Three diaphragm pressure ratios of P 4 /P 1 = 4, 8, and 12 have been employed, where P 4 is the driver gas pressure and P 1 is the pressure within the driven compartment of the shock tube. These lead to incident shock Mach numbers of M, = 1.34,1.54, and 1.66, respectively. The length of the driver section of the shock tube was 700 mm. Air was used for both the driver and driven gases. High-speed shadowgraphy was employed to visualize the induced flowfield. Pressure measurements were taken at different locations along the test section to study the flow quantitatively. The induced flow is unsteady and dependent on the degree of compressibility of the initial shock wave generated by the rupture of the diaphragm.
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