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The tip flow of a part span slotted flap

Published online by Cambridge University Press:  04 July 2016

A. C. Willmer ,
R. V. Barrett  and
J. D. Coleman
A. C. Willmer
Affiliation:
British Aerospace
R. V. Barrett
Affiliation:
University of Bristol
J. D. Coleman
Affiliation:
University of Bristol
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Extract

The work to be described forms part of an experimental study into the overall influence that the end region of a flap has on the flow of a high lift wing system. Here, our attention will be restricted mainly, but not entirely, to the tip flow of the flap itself.

The study has been a collaborative venture over the past three years between British Aerospace-Civil Aircraft Division and the Aerospace Engineering Department of Bristol University, the latter funded by an SER.C research grant. BAe's major contribution was the undertaking of the main test programme, with University participation, using a large swept wing, high lift half model in the Filton low speed wind tunnel. The model was loaned by RAE for the study.

Type
Wing Tip Flows and Wing Devices
Information
The Aeronautical Journal , Volume 91 , Issue 910 , December 1987 , pp. 453 - 469
Copyright
Copyright © Royal Aeronautical Society 1987 

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References

1. Barrett, R. V. Measurements in 3-Dimensional Boundary Layers and Narrow Wakes using a Single Sensor Hot Wire Probe. To be presented — 12th ICIASF (International Conference on Instrumentation for Aerospace Simulation Facilities). Williamsburg, Va. June 1987.Google Scholar
2. El-Ramly, Z. and Rainbird, W. J. Flow survey of the vortex wake behind wings. J Aircraft, September 1977, 14, 11.Google Scholar
3. Pengelly, V., and Ponton, A. J. C. The Effect of Flap End Modifications on the Lift/Drag Ratio for a Wing with a Single Slotted Flap. University of Bristol, Department of Aeronautical Engineering, Undergraduate Report No 349, June 1986.Google Scholar
4. Green, J. A. and Wirdnam, D. A. Investigations into the effects of Flap End Modifications on the Performance of a Wing with a Single Slotted Flap. University of Bristol, Department of Aerospace Engineering, Undergraduate Report No 357, June 1987.Google Scholar