Gas-dynamic losses in the flow part of the channel charge of a solid-propellant rocket engine

Modern methods of computational fluid dynamics have been used to study flows with mass supply in axisymmetric channels solid-propellant rocket motor charges. The studies were carried out the aim increasing accuracy predicting intraballistic parameters for performing engineering calculations. analysis changes characteristics flow part channel charge classical and nozzleless solid propellant motors is different rates from combustion surface. For an isobaric chamber, a characteristic velocity profile shown along tubular path sudden expansion. It that steady cosine axial after expansion channel, length more than three gauges required. high-speed comparison depending on under conditions supply. tendency influence character noted. at Mach number over 0.5, increase rate surface provides less filled tending cosine. differences between pressure losses passage charge, calculated approximation, determined using gas-dynamic functions, are shown. An leads decrease 0.8.