Абстрактный

Computational Analysis of Scramjet Inlet

V. Rajashree, P. Manivannan, G. Dinesh kumar

A numerical study of a hypersonic inlet with varying ramps and different cowl deflections has been made in this paper. This variable geometry inlet has a notable influence in shape and position of the front and cowl shock. Optimising the performance of the inlet is to operate over a range of Mach numbers at the concerned angle of attack. It is to be noted that the flow in hypersonic air-breathing engine is still supersonic at the end of the inlet and before the combustor. The interaction of oblique shock by the inlet ramp in hypersonic flow is observed. This shock may force the boundary layer to separate from the wall, resulting in pressure losses and a reduction of the inlet efficiency. Variable geometry inlets can be used over a relatively wide range of Mach numbers than the fixed geometry inlets. The numerical results are validated here by simulating the flow through a 2-D mixed-hypersonic inlet.