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Published online by Cambridge University Press: 04 July 2016
A method for providing lateral control at supersonic speeds by means of control surfaces located on nacelles or on the fuselage is described. These surfaces are arranged so that they affect the pressures over adjacent wings, and hence produce a rolling moment. The note includes the results of calculations and of a limited number of measurements which enable the effectiveness of such controls to be estimated.
The work described was initiated in 1955. After the paper was submitted for publication it was, however, learned (see Aircraft Engineering, December 1957, page 394) that an analogous scheme has been patented in the U.S.A. by Chance-Vought Aircraft Inc.