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A Study of the Flow Field Associated with a Steadily-Rolling Slender Delta Wing

Published online by Cambridge University Press:  04 July 2016

J. K. Harvey
J. K. Harvey*
Affiliation:
Imperial College of Science and Technology
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Summary

In this paper an experiment is described in which a detailed study was made of the flow field associated with a slender sharp-edged delta wing which was rolling steadily at zero angle of attack to an air stream. The investigation was made by performing two pressure surveys: first , one of the static pressure acting on the wing’s surface and second by measuring the total-head distribution in the neighbourhood of the wing. From the former the local rolling-moment coefficients, Clp, are evaluated and these are compared with the predictions for attached flow, thus assessing the contributions to the forces acting on the wing which arise as a consequence of the leading-edge separations. The second set of surveys is used to construct a picture of the flow-field details and this is compared with that known to occur on a similar wing when it is set at an angle of attack to the airstream. One interesting finding is that the secondary separation which appears to cause the discrepancy between the theoretical predictions and the measurements made on slender wings at incidence, is absent in this configuration and thus it is concluded that these data could be used for a more meaningful test of the theory.

Type
Research Article
Information
The Aeronautical Journal , Volume 68 , Issue 638 , February 1964 , pp. 106 - 110
Copyright
Copyright © Royal Aeronautical Society 1964

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References

Note on page 107 * It is felt that rotating seals are particularly undesirable when very small pressures are encountered and fine tubing is used in the model as is the case here. This is because the pressure sensed at the leak will swamp that acting at the orifice because of the high impedence to flow afforded by the fine tube.

Note on page 108 * A small pitot tube which is mounted within a cylindrical vented duct, see Ref. (4).

Note on page 108 † For < 1 per cent error in total pressure

Note on page 108 ‡ This is the normalised form of the rolling moment loading and which if integrated from x/c = 0 to 1·0 would yield the total rolling moment acting on the wing.