Calculation of Viscosity Coefficient and Thermal Conductivity of High-temperature High-pressure Gas Mixture of Solid Rocket

Abstract

The transport coefficient of a high-temperature high-pressure combustion gas in solid rocket motor are difficult to be estimated and experimentally verificated. To solve the problem, it was considered that the rocket gas contained strong polar components such as H2O, HCl and SO2, and light components such as H2, and the calculation methods of viscosity coefficient and thermal conductivity of these components and their mixtures under high temperature and high pressure were summarized by a large number of literature examples. The viscosity coefficient, thermal conductivities and Prandtl numbers of three main solid propellant gases of double base propellant(DB), composite modified double base propellant(CMDB)and composite propellant(CP)were calculated at different temperatures(1 500~3 800 K)and pressures(8~20 MPa). The power exponential function law of viscosity coefficient and thermal conductivity changing with temperature and the typical values of Prandtl numbers of solid rocket motor gases were obtained. The obtained result has important practical significance for the in-depth study of promoting the transport properties of high temperature high-pressure gas mixtures, simulation on rocket engine combustion and its internal and external flow. The influence of condensed phase on transport properties is not considered.