Abstract
Suppose that curved compression surface of inlet consists of segments. Two curved surfaces formed by equal compression angles of the micro-element segments and a slight increase in the compression angle of the micro-element segments are designed respectively. The numerical simulation method is used to compare the performance of two curved surfaces with the reference three-wedge compression surface. Select NASA classic test data, in order to determine the turbulence model and calculation method chosen by the numerical simulation Fluent software. The results show: the configuration of the segment compression angle deeply affects compression efficiency of the curved surface compression system. Pressure gradient distribution on the compression surface with constant compression angles segments is nearly constant along the incoming flow direction, and the curved compression surface easily resist the separation of the boundary layer compared to three-wedges compression surface. The approximate calculation method of the bending shock profile is given.
Highlights
Inlet is one of the key components of scramjet
Its performance is tightly associated with the compression efficiency of the compression surface formed the inlet
It can be seen from the figure that the static pressure on the compression surface of the two unconventional curved compressing surfaces rises slowly along the flow direction, and are approximately equal pressure gradient
Summary
Its performance is tightly associated with the compression efficiency of the compression surface formed the inlet. How to design compression surface of inlet is very important. Compression ways of conventional inlets are generally axisymmetric compression, two-dimensional plane compression and three-dimensional sidewall compression and so on. The compression method of the inlet using a curved surface compression system has been extensively studied. It is intended to form a compression system with different compression curvatures by studying the different variation laws of the present microelement fold line compression angle, and investigate the static pressure distribution on the wall surface of the compression system
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