DYNAMICS OF TWO-PHASE FLOW IN ROCKET NOZZLES.
Final technical rept. 1 May 61-31 Dec 64.
UNITED TECHNOLOGY CENTER SUNNYVALE CA RESEARCH AND ADVANCED TECHNOLOGY DEPT
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An experimental and theoretical investigation is reported for the axial and radial velocity lag of a dispersed solid phase in accelerating gases. The program objective was to generate basic information and nozzle design criteria for two-phase flow resulting from the combustion of metallized solid propellants. Various analytic studies were performed to study the character of gas-particle flow in a nozzle. The analytic constant lag solution was used to study the character of two-phase flow in the throat region of the nozzle and to predict the geometric effects on characteristics exhaust velocity performance. Also the constant lag solution was employed to show that the effect of particle channeling on c, calculated assuming one-dimensional flow, is negligible. A computer solution was developed to obtain solutions corresponding to given initial and boundary conditions. Detailed discussions of the physical parameters appearing in the equations, i.e., particle drag coefficient, Nusselt number, and particle size, are also presented. Author