The aerodynamic derivatives with respect to rate of yaw for a delta wing with small dihedral at supersonic speeds

dc.contributor.authorHunter-Tod, J. H.
dc.date.accessioned2012-05-15T14:35:32Z
dc.date.available2012-05-15T14:35:32Z
dc.date.issued1949-03
dc.description.abstractExpressions are derives for the yawing derivatives on the assumptions of the linearised theory of flow for a delta wing with small dihedral flying at supersonic speeds at small incidences. The non-dimensional derivatives are numerically decreasing functions of Mach number. The non-dimensional rolling and yawing derivatives are also numerically decreasing functions of aspect ratio. When the wing lies entirely within the apex Mach cone there is a leading edge suction force proportional to incidence which makes a destabilising contribution to the yawing moment and side force which may be of the same magnitude as that from the inducted excess pressure distribution.en_UK
dc.identifier.urihttp://dspace.lib.cranfield.ac.uk/handle/1826/7153
dc.language.isoenen_UK
dc.publisherCollege of Aeronautics, Cranfielden_UK
dc.relation.ispartofseriesCollege Reporten_UK
dc.relation.ispartofseries28en_UK
dc.titleThe aerodynamic derivatives with respect to rate of yaw for a delta wing with small dihedral at supersonic speedsen_UK
dc.typeReporten_UK

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