Numerical Analysis of Transition Effects in 3D Hypersonic Intake Flows

Martin Krause (), Birgit Reinartz () and Marek Behr ()
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Martin Krause: RWTH Aachen University

A chapter in High Performance Computing in Science and Engineering '09, 2010, pp 395-409 from Springer

Abstract: Abstract A combined experimental as well as computational analysis of a complete scramjet demonstrator model has been initiated. The experimental tests will take place under real flight conditions at a hypersonic wind tunnel. Prior to those tests, a numerical analysis of the performance of two possible demonstrator geometries is conducted. In the current paper, the results of the performance analysis for two different two- and three-dimensional intakes employing single and double outer compression ramps as well as side wall compression are discussed. It is shown that the intakes, in combination with a subsequent isolator, are able to generate flow conditions required for stable supersonic combustion using a central strut injector. Furthermore, the effect of boundary layer transition is also discussed.

Keywords: Mach Number; Turbulent Kinetic Energy; Combustion Chamber; Oblique Shock; Mach Number Distribution (search for similar items in EconPapers)
Date: 2010
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Persistent link: https://EconPapers.repec.org/RePEc:spr:sprchp:978-3-642-04665-0_29

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DOI: 10.1007/978-3-642-04665-0_29

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