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Part III: On an incremental problem related to the steady flow about an aerofoil/spoiler configuration

Published online by Cambridge University Press:  04 July 2016

H. B. Tou  and
G. J. Hancock
H. B. Tou
Affiliation:
Department of Aeronautical Engineering, Queen Mary College, University of London
G. J. Hancock
Affiliation:
Department of Aeronautical Engineering, Queen Mary College, University of London
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Extract

In Part II*, an inviscid model using a panel method has been formulated to solve separated flow past a steady aerofoil/spoiler configuration in a low speed stream. In this note, an investigation has been carried out to formulate an incremental model to solve the steady incremental problem when the aerofoil/spoiler changes its geometry by a small mount (eg for a small angular change of the spoiler).

It has been found that to satisfy the incremental boundary conditions on the initial aerofoil/spoiler geometry, incremental changes in the influence coefficients have to be included for the small change in aerofoil/spoiler geometry and the change in separation streamline geometry. A first order procedure is satisfactory; a second order procedure is also presented.

Type
Inviscid theory of two-dimensional aerofoil/spoiler configurations at low speed
Information
The Aeronautical Journal , Volume 91 , Issue 909 , November 1987 , pp. 406 - 410
Copyright
Copyright © Royal Aeronautical Society 1987 

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References

1. Tou, H. B. and Hancock, G. J. On an Incremental Problem Relating to the Steady Flow about an Aerofoil/Spoiler Configuration. QMC EP1057, February 1984.Google Scholar