An lmplicit Algorithm of Thin Layer Equations In Vlscous Transonic,Two-Phase Nozzle Flow

Omitting viscosity along flow direction,we have simplified the dimensionless N-Sequations in arbitrary curved coordinate system as the thin layer equations.Using theimplicit approximate-factorization algorithm to solve the gasphase governing equ-ations and the characteristic method to follow the tracks of particles,we then obtainedthe full coupled numerical method of two-phase.transonic,turbulent flow.Here,particle size may be grouped,the subsonic boundary condition at entry of nozzle is ireatedby quasi-characteristic method in reference plane and the algebraic model is used forturbulent flow.These methods are applied in viscous two-phase flow.calculation of rocket nozzle and in the prediciton of thrust and specific impulse for solid propellant rocket motor.The calculation results are in good agreement with the measurerment values.Moreover,the influences of different particle radius,different particle mass fraction and particle size grouped on flow field have been discussed,and the influences of particle two-dimensional radial velosity component and viscosity on specific impulse ofrocket motor have been analysed.The method of this paper possesses the advantage of saving computer time.More important,the effect is more obvious for the calculation of particle size being grouped is more obvious.