| DOI | Resolve DOI: https://doi.org/10.2514/1.40954 |
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| Author | Search for: Ackerman, J. R.1; Search for: Gostelow, J. P.1; Search for: Rona, A.; Search for: Carscallen, W. E.1 |
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| Affiliation | - National Research Council of Canada. NRC Institute for Aerospace Research
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| Format | Text, Article |
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| Abstract | 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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| Publication date | 2009-09 |
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| Publisher | American Institute of Aeronautics and Astronautics |
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| In | |
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| Language | English |
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| Peer reviewed | Yes |
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| Export citation | Export as RIS |
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| Report a correction | Report a correction (opens in a new tab) |
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| Record identifier | 0142b57d-fb68-4bf6-b972-bcaf66f665c1 |
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| Record created | 2019-03-06 |
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| Record modified | 2020-04-16 |
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