Numerical computations of supersonic inlet flow

Air-breathing propulsion systems for high-speed space travel applications a re studied. Ramjets and scramjets have been identified as potential candida tes. The flow inlets of such systems are modelled with a simulation that ca n predict all complex inlet flow features, including shock due to forebody, multiple shock reflections, normal shock, shock-boundary layer interaction and associated separation for two-dimensional and axisymmetric inlets. Com puted values are in good agreement with experimental data. Copyright (C) 20 01 John Wiley & Sons, Ltd.