Aerothermodynamics of a Turbulent Shock/boundary Layer Interaction in Three-Dimensional Hypersonic Flows

Details Aerothermodynamics of a Turbulent Shock/boundary Layer Interaction in Three-Dimensional Hypersonic Flows Aerothermodynamics of a Turbulent Shock/boundary Layer Interaction in Three-Dimensional Hypersonic Flows

Feb 2005

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2005esasp.563..621m&link_type=abstract

Proceedings of the Fifth European Symposium on Aerothermodynamics for Space Vehicles (ESA SP-563). 8-11 November 2004, Cologne,

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Pressure and heat transfer measurements taken in a Mach 9 flow at Reynolds number of approximately 48 million/metre are presented, showing the effect of three-dimensionality on the flow system. A two-dimensional axisymmetric flow is achieved by aligning a hollow centre body with the axis of an external cowl. Measurements are taken along the centre-body at a pitch of 1mm. Cowl offsets are then introduced to produce crossflows and hence controlled three-dimensional deviations from the axisymmetric case.

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