An upwind scheme based on the unstructured mesh is developed to solve ideal 2-D magnetohydrodynamics （MHD） equations. The inviscid fluxes are approximated by using the modified advection upstream splitting method （...An upwind scheme based on the unstructured mesh is developed to solve ideal 2-D magnetohydrodynamics （MHD） equations. The inviscid fluxes are approximated by using the modified advection upstream splitting method （AUSM） scheme, and a 5-stage explicit Runge-Kutta scheme is adopted in the time integration. To avoid the influence of the magnetic field divergence created during the simulation, the hyperbolic divergence cleaning method is introduced. The shock-capturing properties of the method are verified by solving the MHD shock-tube problem. Then the 2-D nozzle flow with the magnetic field is numerically simulated on the unstructured mesh. Computational results demonstrate the effects of the magnetic field and agree well with those from references.展开更多
Development of an Advection Upstream Splitting Method(AUSM+-up)scheme-based Unstructured Finite Volume(UFVM)solver for the simulation of two-dimensional axisymmetric/planar high speed compressible turbulent reacting s...Development of an Advection Upstream Splitting Method(AUSM+-up)scheme-based Unstructured Finite Volume(UFVM)solver for the simulation of two-dimensional axisymmetric/planar high speed compressible turbulent reacting shear layers is presented.The inviscid numerical flux is evaluated using AUSM+-up upwind scheme.An eight-step hydrogen–oxygen finite rate chemistry model is used to model the development of chemical species in a supersonic reacting flow field.The chemical species terms are alone solved implicitly in this explicit flow solver by rescaling the equation in time.The turbulence modeling has been done using RNG-based k–model.Three-stage Runge–Kutta method has been used for explicit time integration.The nonreacting twodimensional Cartesian version of the same solver has been successfully validated against experimental and numerical results reported for the wall static pressure data in sonic slot injection to supersonic stream.Detailed validation studies for reacting flow solver has been done using experimental results reported for a coaxial supersonic combustor,in which species profile at various axial locations has been compared.Present numerical solver is useful in simulating combustors of high speed air-breathing propulsion devices.展开更多
文摘An upwind scheme based on the unstructured mesh is developed to solve ideal 2-D magnetohydrodynamics （MHD） equations. The inviscid fluxes are approximated by using the modified advection upstream splitting method （AUSM） scheme, and a 5-stage explicit Runge-Kutta scheme is adopted in the time integration. To avoid the influence of the magnetic field divergence created during the simulation, the hyperbolic divergence cleaning method is introduced. The shock-capturing properties of the method are verified by solving the MHD shock-tube problem. Then the 2-D nozzle flow with the magnetic field is numerically simulated on the unstructured mesh. Computational results demonstrate the effects of the magnetic field and agree well with those from references.
文摘Development of an Advection Upstream Splitting Method(AUSM+-up)scheme-based Unstructured Finite Volume(UFVM)solver for the simulation of two-dimensional axisymmetric/planar high speed compressible turbulent reacting shear layers is presented.The inviscid numerical flux is evaluated using AUSM+-up upwind scheme.An eight-step hydrogen–oxygen finite rate chemistry model is used to model the development of chemical species in a supersonic reacting flow field.The chemical species terms are alone solved implicitly in this explicit flow solver by rescaling the equation in time.The turbulence modeling has been done using RNG-based k–model.Three-stage Runge–Kutta method has been used for explicit time integration.The nonreacting twodimensional Cartesian version of the same solver has been successfully validated against experimental and numerical results reported for the wall static pressure data in sonic slot injection to supersonic stream.Detailed validation studies for reacting flow solver has been done using experimental results reported for a coaxial supersonic combustor,in which species profile at various axial locations has been compared.Present numerical solver is useful in simulating combustors of high speed air-breathing propulsion devices.
