Two phase flow of gas-particle mixtures in rocket nozzles was inves¬tigated from a theoretical standpoint, and the governing equations for one-dimensional, two-dimensional, and axisymmetric flow were derived. The characteristic equations for the system were found and put into finite difference form. A numerical solution technique was developed and programed for the IBM 7090 computer. A method was developed for deter¬mining the subsonic flow field based on a one-dimensional sink flow ap¬proximation. The transonic flow field solution was approximated by a power series solution of the linearized system equations for constant kinetic and thermal lags of the particles.
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