Travelling Shock Interaction with Rocket Nozzle
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Abstract
An experimental and numerical study has been undertaken to examine various aspects pertaining to the interaction of an incident travelling axial shock wave with a choked exhaust nozzle for a rocket motor. A cold-flow experiment, based on a shock tube scheme tailored to the present application, proved useful in providing information surrounding the interaction process. Both experimental and numerical results confirmed the existence of substantial transient radial wave activity superimposed on the base reflected axial shock wave. By analogy to actual propulsion system combustion chambers, the transverse wave activity superimposed on the principal axial wave is potentially a factor in supporting an augmentation of the local combustion rate in the aft region of a rocket motor combustor. These results illustrate the potential weaknesses of one-dimensional flow models for certain engineering applications, where important multidimensional phenomena, such as those observed in this study, may not be captured.
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