Infrared measurements of boundary-layer transition on an inclined cone at Mach 6

Aline Van Den Kroonenberg, Rolf Radespiel, Graham Candler, Malte Estorf

Research output: Chapter in Book/Report/Conference proceedingConference contribution

14 Scopus citations

Abstract

Infrared technique was used to visualize cross-flow vortices on a 7° half-angle sharp cone at an angle of attack of 6.6°. The measurements were made in the Mach 6 hypersonic Ludwieg tube Braunschweig of the Technische Universität Braunschweig. Surface pressure-sensors gave additional information of the frequency and the position on the cone of second-mode instabilities. The combined data was used to identify the surface regions where laminar-turbulent transition was caused by second-mode instabilities. Relative N-factors were computed along the footprints of the cross-flow vortices. These N-factors were modified by the placement of artificial roughness elements on the cone's surface.

Original languageEnglish (US)
Title of host publication48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition
PublisherAmerican Institute of Aeronautics and Astronautics Inc.
ISBN (Print)9781600867392
DOIs
StatePublished - 2010

Publication series

Name48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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