SUPERSONIC-FLOW IN ABLATIVE DISCHARGE CAPILLARIES

The Mach number equation for plasma flow in ablative discharge capilla ries was derived from a set of 1-D flow equations which incorporate th e ablation and Ohmic dissipation processes. By examining this equation it is concluded that, while in the case of a capillary with a constan t cross section the flow is subsonic and the sound velocity can be rea ched only at the open end, there is a possibility to reach supersonic plasma velocities inside a capillary with a monotonically increasing c ross-sectional area. (C) 1997 Elsevier Science B.V.