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Cowl Shapes of Minimum Drag in Supersonic Flow

Part 2. Newtonian Optima

Published online by Cambridge University Press:  04 July 2016

E. Angus Boyd
E. Angus Boyd*
Affiliation:
The College of Aeronautics, Cranfield, Bedford
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Extract

In part 1 of this paper the shape of an axially symmetric ducted body, of given length and fineness ratio, having minimum pressure drag was derived using the Newtonian impact pressure law. It was shown that this shape closely approximated that found by a computer method of Guderley, Armitage and Valentine which employed the general flow equations. Indeed the two curves could be distinguished only for values of the diameter ratio Δ=di/df, of the initial and final diameters, so small as to be outside the range likely to be used for cowl shapes.

Type
Research Article
Information
The Aeronautical Journal , Volume 69 , Issue 650 , February 1965 , pp. 121 - 126
Copyright
Copyright © Royal Aeronautical Society 1965

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References

1.Boyd, E. A.Cowl Shapes of Minimum Drag in Supersonic Flow: Part I. Comparison of the Guderley and Newtonian Optima. Journal of the Royal Aeronautical Society, p 46, January 1965.Google Scholar
2.Guderley, K. G., Armitage, J. V. and Valentine, E. M. Nose and Inlet Shapes of Minimum Drag in Supersonic Flow. Aeronautical Research Laboratories, Wright-Patterson Air Force Base, ARL 62-342, 1962.Google Scholar
3.Miele, A. Slender Shapes of Minimum Drag in Newtonian Flow. Zeitschrift für Flugwissenschaften, May 1963.Google Scholar
4.Leitmann, G. (Editor). Optimisation Techniques with Applications to Aerospace Systems, Chapter 4. Academic Press, 1962.Google Scholar