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.