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Part IV: Oscillatory aerofoil/spoiler characteristics

Published online by Cambridge University Press:  04 July 2016

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Summary

A numerical panel method has been developed for the calculation of the two-dimensional potential flow about an aerofoil-spoiler configuration undergoing periodic motions. The cases investigated include a spoiler oscillating in simple harmonic motion on a steady aerofoil, and an aerofoil-spoiler configuration oscillating in overall pitch and normal translation.

The method is a perturbation method about the steady in viscid flow model of an aerofoil-spoiler configuration.

Elements of linear piecewise vorticity are placed on the aerofoil and spoiler surfaces, while the separation streamlines are replaced by elements of uniform vorticity. Time varying vorticities are shed from the spoiler tip and aerofoil trailing edge, along the upper and lower separation streamlines respectively, through the wake closure region, combining in a planar wake downstream of the wake region.

Predicted forces and moments are broadly in agreement with trends of experimental results available in the literature.

Type
Inviscid theory of two-dimensional aerofoil/spoiler configurations at low speed
Information
The Aeronautical Journal , Volume 91 , Issue 909 , November 1987 , pp. 410 - 428
Copyright
Copyright © Royal Aeronautical Society 1987 

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References

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