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High Lift-Drag Ratio Double Wedges of Given Volume which Support Two-Dimensional Supersonic Flow Fields

Published online by Cambridge University Press:  04 July 2016

R. S. Bartlett*
Affiliation:
Aerodynamics Dept, RAE, Farnborough

Extract

Several authors have considered the lifting characteristics of various simple shapes at hypersonic speeds. Non-weiler has dealt with shapes derived from wedge flows, and Townend has considered a class of two-dimensional shapes with concave undersurfaces. Cole and Aroesty and Pike have both considered two-dimensional shapes which are perturbations of simple wedge flow. They show that slightly higher values of the lift-to-drag ratio than that of the wedge are obtainable. Cole and Aroesty apply hypersonic small disturbance theory, under the constraint of constant lift, and suggest that the optimum shape is a “multi-wedge”. They show further that the optimum of a more restricted class of shapes having undersurfaces made of two plane surfaces, has a slightly concave surface. Pike has applied a more accurate (second-order) perturbation theory to a class of shapes which consist of small deviations from a wedge. He finds that the optimum undersurface consists of two plane surfaces, and confirms Cole and Aroesty's result that it must be slightly concave, except perhaps at low Mach numbers below the hypersonic range. It must be remembered that these results depend upon the assumed constraint of constant lift.

Type
Technical Notes
Copyright
Copyright © Royal Aeronautical Society 1970 

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References

1. Nonweiler, T. R. F. Delta Wings of Shapes Amenable to Exact Shock Wave Theory. ARC 22 644, March 1961. Journal of the Royal Aeronautical Society, Vol 67, No 625, January 1963.Google Scholar
2. Townend, L. H. On Lifting Bodies Which Contain Two-dimensional Supersonic Flows. ARC R & M No 3383, 1964.Google Scholar
3. Cole, J. D. and Aroesty, J. Optimum Hypersonic Lifting Surfaces Close to Flat Plates. AlAA Journal, Vol 3, No 8, pp 1520–2, August 1965.Google Scholar
4. Pike, J. Minimum Drag Surfaces of Given Lift Which Support Two-dimensional Supersonic Flow Fields. RAE Tech Report No 66305, September 1966.Google Scholar
5. Küchemann, D. and Weber, J. An Analysis of Some Performance Aspects of Various Types of Aircraft Designed to Fly Over Different Ranges at Different Speeds. RAE Tech Report No 66188, June 1966.Google Scholar
6. Collingbourne, J. R. and Peckham, D. H. The Lift and Drag Characteristics of Caret Wings at Mach Numbers Between 5 and 10. RAE Tech Report No 66036 (ARC 28, 172), February 1966.Google Scholar
7. Crabtree, L. F. Boundary-layer Effects on Hypersonic Aircraft. Unpublished RAE Paper, August 1965. To be published in Jahrb, 1965 d, WGLR.Google Scholar