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dc.contributor.authorEkaterinaris, J.A.
dc.contributor.authorChandrasekhara, M.S.
dc.contributor.authorPlatzer, M.F.
dc.date.accessioned2016-10-03T20:17:48Z
dc.date.available2016-10-03T20:17:48Z
dc.identifier.citationJ.A.Ekaterinaris, M.S.Chandrasekhara, and M.F.Platzer, モAnalysis of Low Reynolds Number Airfoil Flowsヤ, (AIAA Paper 94-0534), Journal of Aircraft, Vol. 32, No. 3, May-Jun. 1995, pp. 625-630.
dc.identifier.urihttp://hdl.handle.net/10945/50074
dc.description(AIAA Paper 94-0534), Journal of Aircraft, Vol. 32, No. 3, May-Jun. 1995, pp. 625-630.en_US
dc.description.abstractCompressible steady and unsteady flowfields over a NACA 0012 airfoil at transitional Reynolds numbers are investigated. Comparisons with recently obtained experimental data are used to evaluate the ability of a numerical solution based on the compressible thin layer Navier-Stokes approximation, augmented with a transition model, to simulate transitional flow features. The discretization is obtained with an upwind-biased, factorized, iterative scheme. Transition onset is estimated using an empirical criterion based on the computed mean flow boundarylayer quantities. The transition length is computed from an empirical formula. The incorporation of transition modeling enables the prediction of the experimentally observed leading-edge separation bubbles. Results for steady airfoil flows at fixed angles of attack and for oscillating airfoils are presented.
dc.publisher
dc.publisherAIAA
dc.rightsThis publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.en_US
dc.titleAnalysis of Low Reynolds Number Airfoil Flowsen_US
dc.typeArticleen_US


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