The Solid Propellant Erosive Combustion (SPEC) Model previously developed by the author has been extended to calculate the flow in a two-dimensional rocket motor. The problem is treated as a confined reacting turbulent boundary layer using a second-order turbulence closure model. Comparison of calculated results with cold-flow experimental data confirms that the development of mean velocity is initially well described by laminar, 'inviscid' theory. However, due to the rapid development of turbulence within the port, transition to a turbulent velocity profile is predicted to occur at center-port Reynolds numbers greater than those obtained in the considered experiments. Transition is also predicted to occur prior to the onset of steady-state erosive burning in actual grain ports. Comparisons of SPEC calculations with measured static pressure distributions are made for a composite propellant 'slab' motor. Best agreement with static pressure data is obtained for propellant roughness heights which are approximately 10 % of the AP crystal diameters. Additionally, theoretical comparisons with the Lenoir-Robillard model show that the SPEC model predicts a much more rapid decrease in erosion as port width (hydraulic radius) is increased. (Se)
Effect of grain port flow on solid propellant erosive burning
Einfluss der Grain Port Duesenstroemung auf die erosive Verbrennung von Feststoff-Raketentreibmitteln
AIAA-Papers ; Jul ; 1-9
1978
9 Seiten, 6 Bilder, 2 Tabellen, 16 Quellen
Conference paper
English
Solid-propellant erosive burning
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