Abstract
The aerodynamic design of hypersonic inlets is a critical issue for the overall performance of an air-breathing propulsion system. The design procedure of basic Busemann inlet is presented. Five truncated Busemann inlets with a contraction ratio of 9 are designed for Mach 6. These inlets have different truncation angles range from 0°to 6°. Numerical simulations have been performed to investigate the effects of truncation on inlet performance. The results of numerical simulations confirmed the good performance of the Busemann inlet. The truncation angle of 4°is preferred.
Highlights
The aerodynamic design of hypersonic inlets is a critical issue for the overall performance of an air-breathing propulsion system
The relative large length and corresponding heavy weight of the basic Busemann inlets prevent it from realistic application
As the truncation angle is increased, an oblique shock is formed at the sharp leading edge
Summary
The aerodynamic design of hypersonic inlets is a critical issue for the overall performance of an air-breathing propulsion system. The inlet of a scramjet engine serves to capture and compress the engine air flow. Many types of hypersonic inlets, such as two-dimensional inlets, axisymmetric inlets and sidewall-compression inlets, have been evaluated There has been a renaissance of the inward turning inlets for hypersonic air-breathing propulsion (Adam Siebenhaar ,2006;Bulman, M.J.,2006). Inward turning inlets derived from efficient compression flowfield offer unique performance. The potential benefits include improved flowpath performance, greater structural efficiency, and great flexibility in vehicle configuration development. Previous work has shown that axisymmetric Busemann and streamtraced Busemann inlets are good candidates for hypersonic air-breathing vehicles. Van Wie (Van Wie, D M, 1992) and Billig
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