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Flying-Hot-Wire Study of 2-Dimensional Mean Flow Past an NACA 4412 Airfoil at Maximum Lift

Coles, D. and Wadcock, A. J. (1978) Flying-Hot-Wire Study of 2-Dimensional Mean Flow Past an NACA 4412 Airfoil at Maximum Lift. Bulletin of the American Physical Society, 23 (8). p. 991. ISSN 0003-0503.

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Hot-wire measurements have been made in the boundary layer, the separated region, and the near wake for flow past an NACA 4412 airfoil at maximum lift. The Reynolds number based on chord was about 1,500,000. Special care was taken to achieve a two-dimensional mean flow. The main instrumentation was a hot-wire probe mounted on the end of a rotating arm. An unexpected effect of rotor interference was identified and brought under control. A digital computer was used to control synchronized sampling at closely spaced points along the probe arc. Ensembles of data were obtained at several thousand locations in the flow field. The data include intermittency, two components of mean velocity, and twelve mean values for double, triple, and quadruple products of two velocity fluctuations. The data are available on punched cards in raw form and also after use of smoothing and interpolation routines to obtain values on a fine rectangular grid aligned with the airfoil chord.

Item Type:Article
Additional Information:© 1978 American Institute of Physics. Research supported by NASA Ames Research Center under Grants NGL 05-002-229 and NSG-2319.
Funding AgencyGrant Number
NASA Ames Research CenterNGL 05-002-229
NASA Ames Research CenterNSG-2319
Issue or Number:8
Record Number:CaltechAUTHORS:20130509-075755948
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Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:38374
Deposited By: Tony Diaz
Deposited On:09 May 2013 20:05
Last Modified:03 Oct 2019 04:56

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