Abstract
A solution to the problem of slender wings in roll about the wind axis and at angle of attack is presented. The basic approach used is a variation of that of Brown and Michael interpreted to take into account the antisymmetrical component in the resultant flow. A pressure distribution function is derived and plotted in a representative range of the key parameters, (p,a,s()) and a general expression for the evaluation of the damping contribution in roll caused by leading-edge separation in slender wings is given. The method is applied here for the evaluation of the roll damping moment and pitch coupling of a basic delta-wing, but the pressure distribution function is given in generalized form. This should enable the flow characteristics on more general rolling configurations to be reliably assessed within the limitation of the model adopted.
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