Experiments on Hypersonic Roughness Induced Transition by Means of Infrared Thermography

Details Experiments on Hypersonic Roughness Induced Transition by Means of Infrared Thermography Experiments on Hypersonic Roughness Induced Transition by Means of Infrared Thermography

Publishing date

Feb 2005

URL

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2005esasp.563..255s&link_type=abstract

Journals

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

Science

Other

Type

Scientific paper

Abstract

Roughness induced boundary layer transition is experimentally investigated in the hypersonic flow regime at M = 9. The primary interest is the possible effect of stepwise geometry imperfections (2D isolated roughness) on (boundary layer) transition which may be caused on the EXPERT vehicle by the difference in thermal expansion due to the different materials used in the vehicle-nose construction. Also 3D isolated and 3D distributed roughness configurations were studied. Quantitative Infra-Red Thermography (QIRT) is used as primary diagnostic technique to measure the surface convective heat transfer and to detect boundary layer laminar-to-turbulent transition. The investigation shows that for a given height of the roughness element, the boundary layer is least sensitive to a step-like disturbance, whereas distributed 3D roughness was found to be effective in triggering transition. The experimental results have been compared to existing hypersonic transition correlations (PANT and Shuttle). Finally a transition criterion is evaluated which is based on the critical roughness height Reynolds number. Usage of this criterion enables a straightforward extrapolation to flight. Key words: hypersonic flow, boundary layer transition.

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