### Kostyushin K.V. Glazunov A.A. Kuvshinov N.E. Eremin I.V. Kagenov A.

## Mathematical modeling of gas dynamics of nanoaluminum application in solid-propellant rocket motor

### Reporter: Kostyushin K.V.

In this work on the basis of mathematical modeling of two-phase flow in rocket engine nozzles on solid propellant a gas-dynamic pattern of a two-phase flow and levels of losses of a specific impulse on a two-phase state are analyzed. A comparison of three methods for calculating the subsystems of the gas-phase equations based on solving the direct and inverse problem of the Laval nozzle was made. For calculation the direct problem of the Laval nozzle the quasi-stable method and the iteration method based on the solution of stationary equations was applied. To solve subsystems of fractional particle equations was implemented stationary and non-stationary method of calculation. The calculations were carried out under various conditions (pressure in the combustion chamber, the weight fraction of the condensate, the diameter of the minimum nozzle throat) in the quasi-one-dimensional approximation with considering coagulation, fragmentation and rotation of the condensate particles. To describe the processes of coagulation was used the model of the "tagged" particles and a polydisperse model fragments. It is shown that the flow pattern and the level of losses of the specific impulse to the two-phase state differ in the cases of a two-modal and one-modal particle sizes distribution functions at the inlet to the nozzle. Coagulation processes for the two-modal function occur more intensively, and the level of two-phase losses with varying proportions of nanodispersed aluminum under equal conditions remains almost at the same level.

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