Massively parallel numerical simulation of a kerosene-fueled scramjet on national MPP computer with 1024 CPUs is presented.A self-developed software AHL3D is employed.Reynolds averaged N-S equations are adopted in governing equations.Inviscid flux is computed with Steger-Warming flux-splitting scheme.Turbulent effects are studied in a k-ω two-equation turbulence model.Kerosene is replaced by a simple surrogated fuel of n-decane.Computed wall pressure along combustor exhibits good agreement with measured data.Computation shows that cavity provides main ignition zone and flame holder,and recirculation zone resulting from fuel injection contributes to flame stability.It indicates that the AHL3D code and methodologies can be used to simulate complicated flow patterns in kerosene-fueled scramjets.

Based on traditional flux method,a source six flux(SSF) model in cylindrical coordinate is proposed for arbitrary directional radiative intensity.Basic theory and numerical procedure of SSF model are presented in detail.Compared with directional radiative intensity by two flux method(TFM) and Backward Monte Carlo(BMC) method in cylindrical media,results of SSF method agree well with those of BMC.However,SSF method is more efficient than BMC,thus SSF method is more suitable in solving directional radiative intensity problems.

A method using CFD technology is used for accurate prediction of aerodynamic force and heat of air-breathing hypersonic vehicles. It includes governing equations, turbulence models, advanced wall boundary condition and transition formulas. Heat flux and skin friction for typical laminar and turbulent flows of air-breathing vehicles are validated. Independence of heat flux and skin friction prediction with normal grids in turbulence flow is confirmed using wall function boundary. Aerodynamic heat and force of a designed air-breathing vehicle are simulated. Reliable numerical data for vehicle aerodynamic design and aerodynamic heat protection are provided.

A recursive-box method is proposed to compute wall distance in a turbulence model. The method is efficient, general and robust. For 3D and 2D problems, compared with a direct method, the recursive-box method obtains similar results and reduces computational time by one order of magnitude. Moreover, the denser the grids are, the higher efficiency of recursive-box is.

The stability, starting problem, initial value of sub-iteration and convergence criterion of implicit iteration of the dual-time stepping method are studied. Analysis of von Neumann stability indicates that in the implicit method employed in sub-iteration real time step is limited by the requirment of stability. Computation on Sod's shock tube validates the conclusion.

The paper introduces a three-dimensional nodal and subchannel analysis code package for the core transient in PWPs-SNENM/RTSP, including the model of neutronics and thermohydraulics used in the package. The preliminary results of applying this code package to the analysis of Steam-Line Break accident for Qinshan NPP are given and also evaluated briefly.