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The Lift of a Slender Combination of a Fuselage of Rectangular Cross-Section with a High Wing

Published online by Cambridge University Press:  04 July 2016

R. D. Andrews
R. D. Andrews*
Affiliation:
Royal Aircraft Establishment, Farnborough
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Extract

In a recent paper, Portnoy discussed the properties of a slender-wing with a slender half-body of revolution mounted beneath it. Another configuration of the same type has a fuselage of rectangular cross-section underneath the wing. The present note gives results for the lift on this class of configurations in attached flow and compares it with that for other wing-body combinations.

Ward's slender-body theory describes the flows about appropriately slender configurations where viscous effects are negligible (i.e. the boundary-layer thickness is small in comparison with the transverse dimensions of the body and no separation occurs upstream of the station under consideration). A restriction of the simplified version used in this note is that no element of a load-bearing surface may be upstream of that station. This implies that the wing span must not decrease in a spanwise direction. Another assumption we make is that no leading-edge separation occurs.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 74 , Issue 719 , January 1977 , pp. 903 - 906
Copyright
Copyright © Royal Aeronautical Society 1970 

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References

1. Portnoy, H. The slender wing with a half body of revolution mounted beneath. The Aeronautical Journal, Vol 72, No. 693, pp 803–807, September 1968.Google Scholar
2. Ward, G. N. Linearised theory of high-speed flow. Chapter 9. Cambridge University Press, 1955.Google Scholar
3. Pitts, W. C, Nielsen, J. N. and Kaattari, G. E. Lift and centre of pressure of wing-body-tail combinations at subsonic, transonic and supersonic speeds. NACA Report 1307, 1957.Google Scholar
4. Von Kármán, Th. and Burgers, J. M. Aerodynamic Theory, editied by Durand, W. F., Vol. II, Division E. Berlin, Julius Springer, 1935.Google Scholar
5. Bartlett, R. S. Slender body theory calculations of the effect on lift and moment of mounting the wing off the fuselage centre-line. ARC 25965, CP 830, 1964.Google Scholar
6. Andrews, R. D. Unpublished Ministry of Technology Report.Google Scholar
7. Ross, A. Jean. The calculation of lateral stability derivatives of slender wings at incidence, including fin effectiveness, and correlation with experiment. ARC 23089, R & M No. 3402, 1965.Google Scholar
8. Sacks, A. H. Aerodynamic forces, moments and stability derivatives for slender bodies of general cross-section. NACA TN 3283, 1954.Google Scholar