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Part VI: The rapid deployment of a spoiler on a two-dimensional aerofoil

Published online by Cambridge University Press:  04 July 2016

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Summary

A method based on the shedding and convecting of discrete vortices has been developed to calculate the transient loading on an aerofoil-spoiler configuration when the spoiler is suddenly deployed to a particular angle. An innovation in the method is the introduction of Kutta conditions at the separation points.

Although the variation of CL with time is highly irregular, qualitative trends can be deduced. For a range of aerofoil angle of incidence and spoiler angle deployment adverse lift effects (ie, when the lift initially increases) have been obtained, similar adverse lift effects have been measured in experiments.

Type
Inviscid theory of two-dimensional aerofoil/spoiler configurations at low speed
Information
The Aeronautical Journal , Volume 91 , Issue 910 , December 1987 , pp. 492 - 498
Copyright
Copyright © Royal Aeronautical Society 1987 

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