Micro-Ramps Flow Characteristics at Mach 1.9 & 5

Saad, M. R.; Che Idris, A.; Lo, K. H.; Kontis, K.

doi:10.1007/978-3-319-16838-8_70

M. R. Saad³,
A. Che Idris³,
K. H. Lo⁴ &
…
K. Kontis⁴

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International Symposium on Shock Waves

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Abstract

The prominent problem faced by the air-breathing propulsion system of supersonic aero-vehicles is the phenomenon known as shock wave- boundary layer interactions (SBLI) which cause boundary layer separation and adverse pressure gradients

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References

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Authors and Affiliations

Faculty of Engineering, Universiti Pertahanan Nasional Malaysia, 57000, Kuala Lumpur, Malaysia
M. R. Saad & A. Che Idris
The School of MACE, The University of Manchester, Sackville St., M60 1QD, Manchester, UK
K. H. Lo & K. Kontis

Authors

M. R. Saad
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A. Che Idris
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K. H. Lo
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K. Kontis
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Editor information

Editors and Affiliations

Department of Engineering Physics, University of Wisconsin, Madison, USA
Riccardo Bonazza
Department of Mechanical Engineering, Georgia Institute of Technology, Atlanta, Georgia, USA
Devesh Ranjan

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Saad, M.R., Che Idris, A., Lo, K.H., Kontis, K. (2015). Micro-Ramps Flow Characteristics at Mach 1.9 & 5. In: Bonazza, R., Ranjan, D. (eds) 29th International Symposium on Shock Waves 2. ISSW 2013. Springer, Cham. https://doi.org/10.1007/978-3-319-16838-8_70

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DOI: https://doi.org/10.1007/978-3-319-16838-8_70
Publisher Name: Springer, Cham
Print ISBN: 978-3-319-16837-1
Online ISBN: 978-3-319-16838-8
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