Rolling Performance of Aircraft: Formulae for Elliptic, Straight‐Tapered and Trapezoidal Wings, Based on the Schrenck Distribution of Lift

FORMULAE and curves arc given for the derivatives lρ and lξ for three types of wing; elliptic, straight tapered and trapezoidal, based on a modified form of the Schrenk distribution of lift. Comparison with experimental curves for the derivatives shows that the method gives good agreement and enables reasonably accurate estimation of the rolling performance of an aircraft to be made.