Abstract
An experimental method applying microwave techniques to obtain continuous measurement of both the shock and contact discontinuities bounding an air plasma generated in a cylindrical hypersonic shock tube is developed. X-band microwave signals excited in the TE11 mode reflect from the moving shock and contact surfaces. The resulting FM interference pattern is demodulated, yielding continuous velocity versus time data. Results depicting subtle detail of velocity behavior, particularly of the shock front, were obtained over a shock Mach number range of 9 to 13.
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