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Impact Theory Calculations of the Lift and Drag of Ducted Bodies

Published online by Cambridge University Press:  07 June 2016

J. Tinkler
J. Tinkler*
Affiliation:
University of Bristol*
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Summary

Newtonian impact theory has been used to estimate the external pressure forces on ducted bodies of rectangular, circular and semi-circular cross section. With an allowance for skin friction (or other incidence-independent drag) it is shown that maximum lift/drag ratios of about three to four are possible with little effect of body geometry provided that short and very divergent, or tall and narrow rectangular ducts are avoided.

Large changes occur in the separate lift and drag at maximum lift/drag ratio and these have to be made compatible with the weight and thrust capacity of the configurations. The maximum lift/drag ratio of a duct can be improved by the addition of wings, especially for a duct with poor lift/drag ratio, but the best overall performance is with a duct of good lift/drag ratio and low drag.

It is anticipated that impact theory underestimates the pressure forces, and hence the lift/drag ratios, which would obtain at finite Mach numbers but the trends with geometrical changes should be reasonably reliable.

Type
Research Article
Information
Aeronautical Quarterly , Volume 13 , Issue 4 , November 1962 , pp. 327 - 348
Copyright
Copyright © Royal Aeronautical Society. 1962

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References

1. Jamison, R. R. Hypersonic Air-Breathing Engines. Hypersonic Flow. Collar, A. R. and Tinkler, J. (Editors). Colston Papers, Vol. XI, Butterworths Scientific Publications, London, p. 391, 1960.Google Scholar
2. Nicholson, L. F. Engine-Airframe Integration. Journal of the Royal Aeronautical Society Vol. 61, p. 711, November 1957.Google Scholar
3. Eggers, A. J. Jr. Some Considerations of Aircraft Configurations Suitable for Long-Range Hypersonic Flight. Hypersonic Flow. Collar, A. R. and Tinkler, J. (Editors). Colston Papers, Vol. XI, Butterworths Scientific Publications, London, p. 369, 1960.Google Scholar