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.
Investigation on a streamtraced hypersonic Busemann inlet
2010-01-01
7 pages
Article (Journal)
Electronic Resource
English
Busemann inlet for hypersonic speeds.
AIAA | 1966
|Investigation on a Truncated Streamline-Traced Hypersonic Busemann Inlet
British Library Conference Proceedings | 2008
|