In order to improve robustness of multi-fluid-channel scheme on average of volume (MFCAV) and overcome its artificial intervention in actual application, a new HLLCM scheme was designed on a moving mesh, which restrains non-physical mesh tangling without artificial intervention. Numerical results show that the HLLCM scheme maintains one-dimensional spherical symmetry on equal-angle-zoned grids which has better numerical effects in keeping mesh quality and energy conservation in complex applications than MFCAV scheme.

A numerical scheme and method deducing "wall heating errors" in computing problems of radially symmetric flow using Lagrangian cell-centered schemes is investigated.Relation between "wall heating error" and modified equations of difference schemes is introduced.With comparision of sound wave approximate Riemann solver and HLL Riemann solver,a new adaptive heat conduction viscosity is introduced to ameliorate "wall heating errors".Numerical experiments show that this viscosity in current scheme provides satisfactory results.

In calculation of multidimensional fluid mechanics problems with numerical schemes that accurately capture contact discontinuity, perturbation near shock wave may increase dramatically. This is called numerical shock instability. In this paper numerical shock instability on shallow water equations is studied. By analyzing linear stability of several numerical schemes, marginal stability of schemes are found having close relation with numerical shock instability. According to eigenvalue analysis, a hybrid method is designed to remedy nonphysical phenomenon by locally modify the original schemes. Numerical experiments show efficiency and robustness of HLLC-HLL hybrid scheme in eliminating shock instability of shallow water equations.

Numerical simulation of transonic viscous flows around RAE2822 2-D airfoil in Gao-Yong compressible turbulence model is presented. Convection terms and diffusion terms are calculated with ROE (flux difference splitting) scheme and CD (center difference) scheme, respectively. Runge-Kutta time marching method is employed to solve space discrete control equations. It predicts accurately pressure coefficients on airfoil surface, mean velocity, location of shock wave and Macb number contours. Shock-wave/boundary layer interaction and translation from laminar flow to turbulence flow on airfoil surface are analyzed. Numerical results agree well with experimental data. It is demonstrated that Gao-Yong compressible turbulence model can be used to simulate transonic viscous flow around an airfoil. A method for location of translation based on theory of orthotropic turbulence viscosity in Gao-Yong compressible turbulence model is presented.

Numerical computation to predict the pulverized-coal diffusion flame using Lagrangian treatment of the gas-solid flow and combustion is implemented. The authors analyse and discuss the gas-particle momemtum, mass and energy transfer processes. A modified scheme for existing computation model is proposed by the authors, which is effective in promoting two phase coupling process and can overcome divergency in computation for high pulverized-coal concentration combustion.