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

Aircraft Engineering and Aerospace Technology

ISSN: 0002-2667

Publication date: 1 June 1948

Abstract

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.

Citation

Roberts, H. (1948), "Rolling Performance of Aircraft: Formulae for Elliptic, Straight‐Tapered and Trapezoidal Wings, Based on the Schrenck Distribution of Lift", Aircraft Engineering and Aerospace Technology, Vol. 20 No. 6, pp. 167-181. https://doi.org/10.1108/eb031643

Publisher

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MCB UP Ltd

Copyright © 1948, MCB UP Limited