| DOI | Trouver le DOI : https://doi.org/10.2514/1.40954 |
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| Auteur | Rechercher : Ackerman, J. R.1; Rechercher : Gostelow, J. P.1; Rechercher : Rona, A.; Rechercher : Carscallen, W. E.1 |
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| Affiliation | - Conseil national de recherches du Canada. Institut de recherche aérospatiale du CNRC
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| Format | Texte, Article |
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| Résumé | A circular cylinder is tested in crossflow over the subsonic speed range. Time-resolved pressure distributions give information on surface pressure fluctuations; the corresponding drag and base drag coefficients are provided. Measured base pressure fluctuations at low Mach numbers are in agreement with the findings of other researchers. Flow changes at higher subsonic velocities andinto the transonic range are described. Illustrations are drawn from the observations of other researchers, enabling physical explanations to be given to assist toward amore generalmodeling of the problem. AtMach numbers above 0.6 the changing strength of the vortices reduces the base drag coefficient up to aMach number of 0.9, at which the onset of sonicflow increases the drag. Strouhal number variation is compared with the measurements of other authors. The paper concentrates on providing reliable measurements of vortex shedding and base pressure over the subsonic speed range rather than attempting to provide universal correlations. |
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| Date de publication | 2009-09 |
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| Maison d’édition | American Institute of Aeronautics and Astronautics |
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| Dans | |
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| Langue | anglais |
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| Publications évaluées par des pairs | Oui |
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| Exporter la notice | Exporter en format RIS |
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| Signaler une correction | Signaler une correction (s'ouvre dans un nouvel onglet) |
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| Identificateur de l’enregistrement | 0142b57d-fb68-4bf6-b972-bcaf66f665c1 |
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| Enregistrement créé | 2019-03-06 |
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| Enregistrement modifié | 2020-04-16 |
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