Two dimensional converging-diverging nozzle is installed in a diaphragm-less shock tube in order to obtain faster flow Mach number. Flow Mach numbers are evaluated from the oblique shock angle emanating from a wedge that is placed in the flow. Uniformity of the flow field is observed by Schlieren high-speed video images. It is found that the flow Mach number of 2.8 is obtained for the test gas of dry air and the helium driver gas. The test time is 4.3 ms and it is long enough to use it as a supersonic wind tunnel. It is more important to delay the arrival of reflected shock wave than just to increase the driver pressure. More work is necessary to establish a numerical method that precisely predict boundary layer separations.
展开▼
