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Rotary Stability Derivatives from Distorted Models

Published online by Cambridge University Press:  04 July 2016

Y. Y. Chan  and
John R. Ward
Y. Y. Chan
Affiliation:
Department of Aeronautics, University of Sydney
John R. Ward
Affiliation:
Department of Aeronautics, University of Sydney
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Extract

Foster and Haynes recently suggested the possibility of measuring the rotary stability derivatives of an aeroplane by testing a suitably distorted model in a wind tunnel. This possibility has been examined for an isolated wing by the authors and has been found to be in error for the derivatives due to rolling and yawing.

In what follows it will be assumed that thin aerofoil theory and Prandtl’s lifting line theory may be applied.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 62 , Issue 568 , April 1958 , pp. 307 - 308
Copyright
Copyright © Royal Aeronautical Society 1958

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References

1.Foster, D. J. and Haynes, G. W. (1956). Rotary Stability Derivatives from Distorted Models. Journal of the Royal Aeronautical Society, September 1956.Google Scholar
2.Glauert, H. (1928). The Lift and Pitching Moment of an Aerofoil due to Uniform Angular Velocity of Pitching. R. and M. 1216, 1928.Google Scholar