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Part V: Steady and oscillatory aerofoil-spoiler-flap characteristics

Published online by Cambridge University Press:  04 July 2016

H. B. Tou  and
G. J. Hancock
H. B. Tou
Affiliation:
Department of Aeronautical EngineeringQueen Mary College, University of London
G. J. Hancock
Affiliation:
Department of Aeronautical EngineeringQueen Mary College, University of London
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Summary

An inviscid model for a steady two-dimensional aerofoil-spoiler at low speeds is applied to an aerofoil-spoiler-plain flap configuration. The model is extended to an aerofoil-spoiler-slotted flap configuration. The flow through a slotted flap can result in either attached flow or separated flow about the flap. The location of the separation point on the flap has to be assumed, it is taken empirically to fit experimental data. The inviscid model is extended to the aerofoil-spoiler-slotted flap configuration with the spoiler oscillating in small amplitude simple harmonic motion about a mean spoiler angle. Although both the steady and unsteady models for the aerofoil-spoiler-flap configuration are crude, the results look encouraging.

Type
Inviscid theory of two-dimensional aerofoil/spoiler configurations at low speed
Information
The Aeronautical Journal , Volume 91 , Issue 910 , December 1987 , pp. 479 - 492
Copyright
Copyright © Royal Aeronautical Society 1987 

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References

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