Print Email Facebook Twitter Comparison of boundary layer calculations for the root section of a wing Title Comparison of boundary layer calculations for the root section of a wing Author Lindhout, J.P.F. van den Berg, B. Elsenaar, A. Institution National Aerospace Laboratory NLR Date 1981-03-06 Abstract At the workshop nine participants presented the results of their calculations for a practical test case. The test case deals with the 3D turbulent boundary layer development, including separation, on the root section of a swept wing. The employed calculation methods comprise 3D integral methods as well as field methods. A short description of each method is given and the results are discussed. It is concluded that all participants are able to predict the flow globally correct. There is a large variation, however, in the details of the results. Subject computational fluid dynamicsturbulent boundary layerboundary layer separationthree dimensional flowswept wingswing rootsviscous flowpartial differential equationsnumerical integrationscomputer programsflow visualizationflow patterns To reference this document use: http://resolver.tudelft.nl/uuid:a0a87657-15bd-444e-a8d0-992c78fa237c Publisher Nationaal Lucht- en Ruimtevaartlaboratorium Access restriction Campus only Source NLR MP 80028 U Part of collection Aerospace Engineering Reports Document type report Rights (c)1981 National Aerospace Laboratory NLR Files PDF 80028.pdf 25.34 MB Close viewer /islandora/object/uuid:a0a87657-15bd-444e-a8d0-992c78fa237c/datastream/OBJ/view