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Some hypersonic intake studies

Published online by Cambridge University Press:  03 February 2016

F. Lanson  and
J. L. Stollery
F. Lanson
Affiliation:
College of Aeronautics, Cranfield University, Bedford, UK
J. L. Stollery
Affiliation:
College of Aeronautics, Cranfield University, Bedford, UK
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Abstract

A ‘two dimensional’ air intake comprising a wedge followed by an isentropic compression has been tested in the Cranfield Gun Tunnel at Mach 8·2. These tests were performed to investigate qualitatively the intake flow starting process. The effects of cowl position, Reynolds number, boundary-layer trip and introduction of a small restriction in the intake duct were investigated. Schlieren pictures of the flow on the compression surface and around the intake entrance were taken. Results showed that the intake would operate over the Reynolds number range tested.

Tests with a laminar boundary layer demonstrated the principal influence of the Reynolds number on the boundary-layer growth and consequently on the flow structure in the intake entrance. In contrast boundary layer tripping produced little variation in flow pattern over the Reynolds number range tested. The cowl lip position appeared to have a strong effect on the intake performance. The only parameter which prevented the intake from starting was the introduction of a restriction in the intake duct.

The experimental data obtained were in good qualitative agreement with the CFD predictions. Finally, these experimental results indicated a good intake flow starting process over multiple changes of parameters.

Type
Research Article
Information
The Aeronautical Journal , Volume 110 , Issue 1105 , March 2006 , pp. 145 - 156
Copyright
Copyright © Royal Aeronautical Society 2006 

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References

1. Cain, T. and Walton, C., The sustained hypersonic flight experiment, AIAA Paper 2003-7030, 12th AIAA International Space Planes and Hypersonic Systems and Technologies, Norfolk Virginia, USA 15-19 December 2003.Google Scholar
2. Needham, D.A., Laminar Separation in Hypersonic Flowd. PhD Thesis, University of London, 1965.Google Scholar
3. Needham, D.A., Progress report of the Imperial London College hypersonic gun tunnel. Imperial College of Science and Technology, Aero-TN 118, 1963.Google Scholar
4. Perigo, D., Shock Waves-Boundary Layer Interactions in a 2D Hypersonic Inlets. MSc Thesis, Cranfield University, College of Aeronautics, 1996.Google Scholar
5. Vannahme, M., Roughness Effects on Flap Control Effectiveness at Hypersonic speeds. MSc Thesis, Cranfield University, College of Aeronautics, 1994.Google Scholar
6. Prince, S.A., Hypersonic Turbulent Interaction Phenomena and Control Flap Effectiveness. MSc Thesis, Cranfield University, College of Aeronautics, 1995.Google Scholar
7. Stollery, J.L., Hypersonic viscous interaction on curved surfaces, Ohio: Wright-Patterson Air Force Base, 1970. J Fluid Mechanics, 1970, 43, (3), pp 497–497.Google Scholar
8. Bachchan, N. and Hillier, R., Hypersonic Inlet Flow Analysis at Off-Design Conditions. AIAA Paper 2004-5380, 2004.Google Scholar
9. Bachchan, N. and Hillier, R., Effects of hypersonic inlet flows non-uniformities on stablising isolator shock systems. AIAA Paper 2004 – 4716, 2004.Google Scholar