The Aerodynamic Derivatives with respect to Rate of Yaw for a Delta Wing with Small Dihedral at Supersonic Speeds

Expressions are derived 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 incidence. The non-dimensional derivatives are numerically decreasing functions of Mach number. The nondimensional rolling and yawing derivatives are also numerically...

The elastic stability of sandwich plates

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.

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

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...

Bound and trailing vortices in the linearised theory of supersonic flow, and the downwash in the wake of a delta wing

The field of flow round a flat aerofoil at incidence can be regarded in linearised theory as the result of both bound and trailing vortices for supersonic as well as for low speed flight. This leads to a convenient method, given the lift distribution over an aerofoil, for calculating the flow round it at supersonic speeds. As an application of...