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Prediction of the lift and moment on a slender cylinder-segment wing-body combination

Published online by Cambridge University Press:  04 July 2016

K. R. Crowell  and
C. T. Crowe
K. R. Crowell
Affiliation:
Department of Mechanical Engineering, Washington State University
C. T. Crowe
Affiliation:
Department of Mechanical Engineering, Washington State University
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Extract

The design of a vehicle with cruise capability which can be packaged in a volume limited space, such as a cylindrical tube, centres around the problem of folding the lifting and control surfaces in such a manner that their deployment is simple and reliable. Several folding schemes are illustrated in Fig. 1. A wing fabricated of a flexible material and suspended by lines from the fuselage (parawing, Fig. 1a) can be folded to occupy only a small volume. These wings, however, are difficult to deploy at high forward speeds and have characteristically poor lift/ drag ratios unsuitable for high performance cruise capability. Another concept which allows storing the wing in a volume-limited space is the “scissor” wing (Fig. 1b) which, when deployed, swings out from a cavity in the fuselage.

Type
Technical notes
Information
The Aeronautical Journal , Volume 77 , Issue 750 , June 1973 , pp. 295 - 298
Copyright
Copyright © Royal Aeronautical Society 1977 

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References

1. Ormiston, R. A. Theoretical and experimental aerodynamics of the sailwing. Journal of Aircraft, Vol 8, No 2, p 77–84 (1971).Google Scholar
2. Pitts, W. C, Nielsen, J. N., Kaattari, G. E. Lift and center of pressure of wing-body-tail combinations at subsonic speeds. NACA Rept 1307 (1957).Google Scholar
3. Ashley, H. and Landahl, M. T. Aerodynamics of Wings and Bodies. Addison-Wesley Pub. Co. (1965).Google Scholar
4. Ward, G. N. Linearised Theory of High Speed Flow. Cambridge University Press (1955).Google Scholar
5. Bartlett, R. S.Slenderbodytheorycalculationsof the effect on lift and moment of mounting the wing off the fuselage centre-line. ARC 25965. CP 830 (1964).Google Scholar
6. Spreiter, J. R. The aerodynamic forces on slender plane-andcruciform-wingandbodycombination.NACA Report 962 (1950).Google Scholar
7. Pachamus, E. C. Predictions of vortex lift characteristics by a leading-edge suction analogy. Journal of Aircraft, Vol 8, No 4, p 193–199 (1971).Google Scholar
8. Smith, J. H. B. Improved calculations of leading-edge separation from slender delta wings. TR 66070, Royal Aircraft Establishment (1966).Google Scholar