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Lateral Control at Supersonic Speeds by means of Control Surfaces on Nacelles or on the Fuselage*

Published online by Cambridge University Press:  04 July 2016

D. W. Holder  and
R. C. Lock
D. W. Holder
Affiliation:
Aerodynamics Division, National Physical Laboratory
R. C. Lock
Affiliation:
Aerodynamics Division, National Physical Laboratory
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Extract

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.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 62 , Issue 570 , June 1958 , pp. 446 - 449
Copyright
Copyright © Royal Aeronautical Society 1958

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Footnotes

*

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.

References

1.Mitchell, M. H. (1950). Effects of varying the size and location of trailing-edge flap-type controls on the aerdynamic characteristics of an unswept wing at a Mach number of 19. N.A.C.A. RM L50F08, August 1950Google Scholar