Computational Analysis of Thermal Compression Effects in a Supersonic Inlet

University of Utah

The inlet area contraction ratio of a scramjet engine is one of the most important parameters in determining engine performance. A thermal compression inlet is studied in which one surface of an internal-external compression inlet is replaced by a high-pressure jet of combustion gases. The inlet flowfield is calculated using a two-dimensional computer model. The thermal compression inlet is shown to eliminate the boundary layer-shock wave interaction which normally limits inlet contraction ratios of the internal-external compression inlets used at high flight Mach numbers. In addition, studies suggest that the level of compression can be controlled by varying the pressure of the compression jet.