Low speed aerodynamic characteristics of 60 degrees rounded leading-edge delta wing with vortex flaps

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dc.contributor.author Rinoie, K. en_UK
dc.date 1996 en_UK
dc.date.accessioned 2005-11-23T12:21:27Z
dc.date.available 2005-11-23T12:21:27Z
dc.date.issued 1996 en_UK
dc.identifier.uri http://hdl.handle.net/1826/229
dc.description.abstract Low speed wind tunnel studies have been conducted to investigate the effect of vortex flaps with a rounded leading-edge on delta wing performance. Measurements were done using the 60º delta wing at a Reynolds number based on the centre line chord 8x10(5). Results indicated that the rounded leading-edge delta wing with 30º vortex flap deflection improves the lift/drag ratio at lift coefficients higher than 0.4, when compared with the sharp leading-edge flat delta wing. The effect of a trailing-edge flap with vortex flaps was also investigated. en_UK
dc.description.sponsorship The University en_UK
dc.format.extent 1963 bytes
dc.format.extent 1302767 bytes
dc.format.mimetype text/plain
dc.format.mimetype application/pdf
dc.language.iso en_UK en_UK
dc.relation.ispartofseries College of Aeronautics Report;9611 en_UK
dc.relation.ispartofseries CU/CoA/R;9611 en_UK
dc.title Low speed aerodynamic characteristics of 60 degrees rounded leading-edge delta wing with vortex flaps en_UK
dc.type Technical Report en_UK


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