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Limitations of the Sonic Area Rule

Published online by Cambridge University Press:  07 June 2016

L. M. Sheppard
L. M. Sheppard*
Affiliation:
Weapons Research Establishment, South Australia
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Summary

Recent free flight tests have provided information on the applicability of the sonic area rule to non-lifting configurations. An analysis of results for the sonic wave drag of swept-back, tapered wings has suggested that the sonic area rule is applicable to thin wing and slender body combinations provided that the product of the wing span/length ratio and the cube root of the thickness /chord ratio is less than unity. The wing span/length ratio was found to be a much more useful slenderness parameter than the aspect ratio.

When the wing has a round-nosed section, theoretical considerations predict the existence of a so-called leading edge drag force varying with Mach number. One would expect such a wing to have the same sonic drag-rise as the equivalent body with an identical cross-sectional area distribution. Some test results do not confirm this drag-rise equivalence. It appears that the transonic drag-rise of the leading edge force is much greater than that predicted by theory.

Tests on one basic wing-body combination, with different body cross-sectional shapes of the same area, suggest that the cross-sectional shape, of a smooth slender body, has no influence on the transonic wave drag of a configuration.

Type
Research Article
Information
Aeronautical Quarterly , Volume 11 , Issue 3 , August 1960 , pp. 248 - 254
Copyright
Copyright © Royal Aeronautical Society. 1960

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References

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