Abstract
A burning propellant at the end of a shock tube in the quiescent-gas zone sees a shock wave primarily as a pressure step. The burning rate is assumed to be surface-temperature-dependent. The time-dependent temperature distribution in the propellant is determined numerically. Burning-rate–time plots are presented for the variation of the important parameters. The effect of initial burning rate is discussed and it is suggested that this effect may bound the allowable frequency regions in solid-propellant combustion instability.
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