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Non-Linear Theory for Slender Wings in Sudden Plunging Motion

Published online by Cambridge University Press:  07 June 2016

B. D. Dore
B. D. Dore*
Affiliation:
Aerodynamics Division, National Physical Laboratory
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Summary

A theoretical treatment is considered for the flow past slender wings in sudden plunging motion when leading-edge vortices are present. A form of slender-wing theory is used and, although the basis of the theory involves no restriction on compressibility, it has proved possible to make calculations only for an incompressible fluid.

Use is made of an analogy between the unsteady flow and related steady flows. In the incompressible case, an extension of the theory of Brown and Michael is given to determine the strength of the vortex and its path from the leading edge to the final steady-state position. A qualitative comparison with experiment is made of the instantaneous position of the vortex. In a typical case the lift is calculated to remain within one per cent of its final value after the vortex strength has reached 55 per cent of its final value.

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Type
Research Article
Information
Aeronautical Quarterly , Volume 17 , Issue 2 , May 1966, pp. 187 - 200
Copyright
Copyright © Royal Aeronautical Society. 1966

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References

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