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.

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