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dc.contributor.authorWeber, Stefan
dc.contributor.authorPlatzer, Max F.
dc.date.accessioned2016-02-25T18:33:54Z
dc.date.available2016-02-25T18:33:54Z
dc.date.issued1999
dc.identifier.citationPresented at the International Gas Turbine & Aeroengine Congress & Exhibition, Indianapolis, Indiana, June 7-10, 1999, Paper 99-GT-21en_US
dc.identifier.urihttp://hdl.handle.net/10945/48030
dc.description.abstractThe static and dynamic stall behavior of the supercritical NLR 7301 airfoil is analyzed with a 2D thin-layer Navier-Stokes code. The code solves the compressible Reynolds-averaged Navier-Stokes equations with an upwind biased numerical scheme in combination with the Baldwin-Lomax or the Baldwin-Barth turbulence models. The effect of boundary layer transition is incorporated using the transition length model of Gostelow et al. The transition onset location is determined with Michel's formula or it can be specified as an input parameter. The two turbulence models yield significantly different steady-state lift coefficients at incidences greater than 8 degrees. Also, the lift hysteresis loops are strongly affected by the choice of the turbulence model. The use of the one-equation Baldwin-Barth model together with the Gostelow transition model is found to give substantially better agreement with the experimental data of McCroskey et al. than the Baldwin-Lomax model.en_US
dc.description.sponsorshipDeutsche Forshungsgemeinschaft (DFG) and the Naval Postgraduate Schoolen_US
dc.format.extent10 p.en_US
dc.publisherMonterey, California. Naval Postgraduate Schoolen_US
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.titleSteady and stall analysis of the NLR 7301 airfoilen_US
dc.typeConference Paperen_US
dc.contributor.corporateNaval Postgraduate School (U.S.)en_US
dc.contributor.departmentAeronautics and Astronauticsen_US


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