Simulation of a Practical Scramjet Inlet Using Shock-Unsteadiness Model
The main function of a scramjet inlet is to capture air flow from the incoming hypersonic stream, compress it through a series of shocks or compression waves, and provide uniform flow to the combustor. There should be maximum mass capture along with a minimum stagnation pressure loss in the inlet.
The shock waves in the inlet duct interact with the boundary layer on the walls and can result in flow separation due to strong adverse pressure gradient across the shock wave. The shock/boundary-layer interaction often results in a complex flow pattern, comprising of additional shocks, expansion waves, shear layer and separation bubble. The separation bubbles are highly viscous, and hence increase the stagnation pressure loss. Peak values of pressure, skin friction and heat transfer rates are found at reattachment point. Also, the separation bubble acts as a blockage to the flow inside the inlet duct and can result in inlet unstart. It is therefore important to predict the shock/boundary-layer interactions in a scramjet inlet, including the size of the recirculation region, accurately.
KeywordsIncident Shock Separation Bubble Oblique Shock Separation Shock Inlet Duct
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