Abstract
Understanding the supersonic jet interactions in a plenum chamber is essential for the design of hot launch systems. Static tests were conducted in a small-scale rocket motor ioaded with a typical nitramine propellaiit to produce a nozzle exit Mach number of 3. This supersonic jet is made to interact with plenum chambers having both open and closed sides. The distance between the nozzle exit and the back piate of plenum chamber are varied from 2. 5 to 7. 0 times the nozzle exit diameter. The pressure rise in the plenum chamber was measured using pressure transducers mounted at different locations. The pressure-time data were analysed to obtain an insight into the flow field in the plenum chamber. The maximum pressure exerted on the back piate of plenum chamber is about 25-35 per cent. of the maximum stagnation pressure developed in the rocket motor. Ten static tests were carried out to obtain the effect of axial distance between the nozzle exit and the plenum chamber back piate, and stagnation pressure in the rocket motor on the flow field in the open-sided and closed-sided plenum chambers configurations.
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