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Smooth leading edge transition in hypersonic flow

Gaillard, L. and Bénard, Emmanuel and Alziary de Roquefort, Thierry Smooth leading edge transition in hypersonic flow. (1999) Experiments in Fluids, 26 (1-2). 169-176. ISSN 0723-4864

(Document in English)

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Official URL: http://dx.doi.org/10.1007/s003480050276


The boundary layer transition along the attachment line of a smooth swept circular cylinder in hypersonic flow is investigated in a blowdown wind tunnel. A wide range of spanwise Mach numbers Me (3.28 to 6.78) is covered with the help of different models at several sweep angles (60 degrees less than or equal to Lambda less than or equal to 80 degrees). The transition is indirectly detected by means of heat flux measurements. The influence of the wall to stagnation temperature ratio is investigated by cooling the model with liquid nitrogen.

Item Type:Article
Additional Information:Thanks to Springer editor. The definitive version is available at http://www.springerlink.com The original PDF of the article can be found at Experiments in Fluids website: http://www.springerlink.com/content/3bttydh5r9ra9u8m/
Audience (journal):International peer-reviewed journal
Uncontrolled Keywords:
Institution:French research institutions > Centre National de la Recherche Scientifique - CNRS (FRANCE)
Other partners > ISAE-ENSMA Ecole Nationale Supérieure de Mécanique et d'Aérotechnique (FRANCE)
Université de Toulouse > Institut Supérieur de l'Aéronautique et de l'Espace - ISAE-SUPAERO (FRANCE)
Other partners > Université de Poitiers (FRANCE)
Laboratory name:
Deposited On:07 Sep 2011 08:57

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