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Response in Yaw

Published online by Cambridge University Press:  28 July 2016

E. J. N. Archbold  and
Kieran T. McKenzie
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Summary

If the motion of an aircraft is restricted, near the ground, to zero bank, comparatively simple solutions to the resulting equations of motion can be obtained, enabling the response to an applied yawing moment to be calculated rapidly. In this paper the analysis is made for three simple forms of applied yawing moment. From the results obtained in a particular case it is possible to judge the suitability of the fin and rudder design chosen on the basis of maximum sideslip reached. A general curve of overswing, in terms of the aerodynamic derivatives of the aircraft, enables the maximum sideslip to be calculated rapidly in a particular case.

Because of typogiaphical difficulties the symbols ^ have been replaced by ° with v, r and t throughout the paper.

Type
Research Article
Information
The Aeronautical Journal , Volume 50 , Issue 424 , April 1946 , pp. 275 - 286
Copyright
Copyright © Royal Aeronautical Society 1946

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References

(1) R. & M. 1801 Nomenclature for stability coefficients. Bryant, L. W., B.Sc., and Gates, S. B., M.A., October, 1937.Google Scholar