Print Email Facebook Twitter Numerical simulation of leading-edge vortex flow Title Numerical simulation of leading-edge vortex flow Author Hoeijmakers, H.W.M. Institution National Aerospace Laboratory NLR Date 1991-11-30 Abstract An analysis is presented of results of a computational method to simulate the steady compressible vortical type of flow around a 65-deg sharp-edged cropped delta wing. The discussion emphasizes some more fundamental aspects of the numerical simulation such as the separation of the flow, the structure of the leading-edge vortex core and the flow inside the free shear layer closed-form solutions are presented which might assist in the analysis of the numerical results. Subject Sharp leading edgesSubsonic flowEuler equations of motionDelta wingsVorticesSeparated flowVortex breakdownInviscid flowComputational fluid dynamicsAngle of attackFinite volume methodComputational gridsKutta-Joukowski condition To reference this document use: http://resolver.tudelft.nl/uuid:6a6dbf72-9d2b-4fb6-ba04-c7fc7659880d Publisher Nationaal Lucht- en Ruimtevaartlaboratorium Access restriction Campus only Source NLR Technical Publication TP 91471 U Part of collection Aerospace Engineering Reports Document type report Rights (c)1991 National Aerospace Laboratory NLR Files PDF 91471.pdf 20.21 MB Close viewer /islandora/object/uuid:6a6dbf72-9d2b-4fb6-ba04-c7fc7659880d/datastream/OBJ/view