Design and Test of a Low Drag Hypersonic Intake

Matthews, Alexander; Jones, T. V.; Cain, T. M.

doi:10.2514/6.2003-7045

Cited by 2 publications

(1 citation statement)

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“…The inlet has been emphasized and studied by many research institutions in the world. Up to now various kinds of inlets have been proposed, including the two-dimensional (2D) planar inlet [1], the axisymmetric inlet [2], and the sidewall compression inlet [3,4]. The axisymmetric inlet is usually used with missiles whose figures are often restricted; planar and sidewall compression inlets, which can take full advantage of the precompression of forebody, adapt to hypersonic airplanes and aerospace planes.…”

Section: Introductionmentioning

confidence: 99%

Investigation on a streamtraced hypersonic Busemann inlet

Sun

Zhang

Wang

et al. 2009

Proceedings of the Institution of Mechanical Engineers, Part G:

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Wind-tunnel testing and numerical simulation of a streamtraced hypersonic Busemann inlet were conducted at Mach 5.3 to investigate the flowfield characteristics and performance of this fixed-geometry inlet at conditions of design point. Wind-tunnel testing was also conducted at Mach 3.85 to investigate the starting and back-pressure limits of this inlet at conditions well below the design point. Results showed that the inlet could self-start at two tunnel conditions. At Mach 5.3, the inlet captured about 90 per cent of available air, generated a compression ratio of 29.9, and withstood a back-pressure ratio of 89 relative to tunnel static pressure; large separation of flow near the cowl closure resulted in flow at the exit of the inlet consisting of a majority of boundary layer by area. At Mach 3.85, the inlet generated a compression ratio of 11.92, captured about 83 per cent of available air, and withstood a back-pressure ratio of up to 34.3 relative to tunnel static pressure.

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