Print Email Facebook Twitter Boundary-layer calculations on the leeward surface of a slender delta wing at incidence Title Boundary-layer calculations on the leeward surface of a slender delta wing at incidence Author de Bruin, A.C. Institution National Aerospace Laboratory NLR Date 1983-12-22 Abstract The three dimensional flow field around delta wings with leading-edge vortex flow can be computed with panel methods. However, secondary flow separation may occur on the leeward surface of the wing. The associated free vortex sheet can be modeled in the potential flow calculation method, if the location of the secondary separation is provided by a boundary layer calculation method. Subject computational fluid dynamicspotential flowthree-dimensional boundary layercompressible boundary layerlaminar boundary layerturbulent boundary layerboundary layer separationdelta wingspressure distributionvortex sheetsleading edgessecondary flowcomputational gridscomputer programsrun time (computers)data storage To reference this document use: http://resolver.tudelft.nl/uuid:a6de02bc-1564-43ab-83b0-8981ccd96191 Publisher Nationaal Lucht- en Ruimtevaartlaboratorium Access restriction Campus only Source NLR-TR 84001 U Part of collection Aerospace Engineering Reports Document type report Rights (c) 1984 National Aerospace Laboratory NLR Files campus only