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The Pressure Distribution at Low Speeds on Two-Dimensional Aerofoils with Blunt Trailing Edges at Zero Incidence

Published online by Cambridge University Press:  04 July 2016

D. J. Maull
D. J. Maull*
Affiliation:
Engineering Laboratory, Cambridge University
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Extract

For the past few years there has been some interest in aerofoils with blunt trailing edges but most work has been associated with the investigation of the base pressure and the pressure distribution on the aerofoil has received little attention. Nash proposed a method of calculating the pressure distribution on aerofoils with blunt trailing edges in the absence of a vortex street, that is with the vortex street suppressed by means of a splitter plate or base bleed. He assumed that the wake of the aerofoil could be taken into account in the calculation by specifying a pressure distribution along the wake and then applying thin aerofoil theory to the aerofoil and wake. This leads to a mixed boundary problem with the aerofoil shape and the wake pressure distribution specified and the calculation is laborious.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 70 , Issue 667 , July 1966 , pp. 727 - 729
Copyright
Copyright © Royal Aeronautical Society 1966

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References

1. Nash, J. F. An Analysis of the Subsonic Flow Past Symmetrical Blunt-Trailing-Edge Aerofoil Sections at Zero Incidence in the Absence of a Vortex Street. To be published in the Aero Res Coun R & M Series. (See also NPL Aero Report 1112, August 1964.)Google Scholar
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