The aerodynamic derivatives with respect to sideslip for a delta wing with small dihedral at supersonic speeds Addendum

The aerodynamic derivatives with respect to sideslip for a delta wing with small dihedral at supersonic speeds Addendum

Robinson, A.
Hunter-Tod, J.H.

College of Aeronautics Cranfield

1947-12-31

Expressions are derived for the sideslip derivatives on the assumptions of the linearised theory of flow for a delta wing with small dihedral flying at supersonic speeds. A discussion is included in the appendix on the relation between two methods that have been evolved for the treatment of aerodynamic force problems of the delta wing lying within its apex Mach cone. When the leading edges are within the Mach cone from the apex, the pressure distribution and the rolling moment are independent of Mach number but dependent on aspect ratio. There is a leading edge suction, which is a function of incidence, aspect ratio and Mach number, that contributes as well as tho surface pressure distribution to the sideforce and yawing moment. When the leading edges are outside the apex Mach cone, the non-dirmensional rolling derivative is, in contrast to tho other case, dependent on Mach numbor arid independent of aspect ratio: the other derivatives and the pressure, however, are dependent on both variables. There is no leading edge suction force in this case. The College of Aeronautics was founded in 1946 and was granted university status in 1969 becoming the Cranfield Institute of Technology. In 1993 it changed its name to Cranfield University.

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