Abstract
Scramjet operation in the lower hypersonic regime between Mach 4 and 7 is characterized by what is called dual-mode combustion. In this situation, the backpressure generated by heat release in the combustor separates the wall boundary layer upstream of fuel injection, forming a highly complex flow known as a pseudoshock. The pseudoshock phenomenon has been studied extensively in the experimental literature, and its structure has been found to be affected by the duct Mach number, the extent of the wall boundary layer, and the streamwise area distribution of the duct. This paper presents a quasi-one-dimensional analysis technique for calculating the flow through a pseudoshock. It is quite general, and it can be used for ducts with any supersonic inflow, cross-sectional shape, and streamwise area distribution. Comparison of the results of this analysis with experimental data indicates that it provides a good estimate of both the interaction length and the pressure distribution for -type pseudoshocks that occur in ducts with Mach numbers above two.
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