Print Email Facebook Twitter A calculation method of the viscous flow around multi-component airfoils Title A calculation method of the viscous flow around multi-component airfoils Author Oskam, B. Institution National Aerospace Laboratory NLR Date 1980-09-20 Abstract The viscous flow around multi-component airfoils has been calculated by solving incompressible potential flow and boxindary layer problems iteratively. The potential flow problem is solved by a revised version of the 2D NLR panel method. A model transport equation of turbulent stress is employed to calculate the turbulent boundary layer. The inviscid/viscous interaction near the trailing edge is treated by matching at the edge of the boundary layer. A treatment of laminar separation bubbles is included. The resultant predictions of the viscous flow agree reasonably well with experimental data, provided no extensive flow separation and/or wake flows in adverse pressure gradient are present. To extend the range of applicability of the present analysis future work should be directed towards the development of a method of analysis for asymmetric wakes and merging shear layers. Subject Computational Fluid DynamicsMulti-element airfoilsLift devicesWing panelsSingularity methods (mathematics)Potential flowtwo-dimensional flowseparated flowturbulent boudary layersviscous flowinviscid flowpressure distributionmixing length flow theoryfinite difference theorymatching To reference this document use: http://resolver.tudelft.nl/uuid:cd5264ef-d19f-4e73-bfd4-734b8df4e92f Publisher Nationaal Lucht- en Ruimtevaartlaboratorium Access restriction Campus only Source NLR-TR 79097 U Part of collection Aerospace Engineering Reports Document type report Rights (c) 1980 National Aerospace Laboratory NLR Files PDF NLR_TR_79097_U.pdf 50.66 MB Close viewer /islandora/object/uuid:cd5264ef-d19f-4e73-bfd4-734b8df4e92f/datastream/OBJ/view