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A Note on the Wave Drag of “Exposed” Rectangular Wings*

Published online by Cambridge University Press:  04 July 2016

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

This Note Gives a simple relationship between the zero-lift wave drag of the wing of a rectangular wing and body combination and the wave drag of the portion of the gross wing blanketed by the body, both evaluated as if isolated (i.e. ignoring the interference of other parts of the combination). The result is valid only when the tip Mach cones of the wing lie downstream of the blanketed wing. Detailed results are given for the case of wings with double-wedge section, the maximum thickness being at mid-chord.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 62 , Issue 568 , April 1958 , pp. 306 - 307
Copyright
Copyright © Royal Aeronautical Society 1958

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Footnotes

*

The work described in this note was carried out while the author was at the Royal Aircraft Establishment, and appeared as RAE Tech. Note Aero 2494.

References

1.Sheppard, L. M. (1957). Methods for Determining the Wave Drag of Non-Lifting Wing-Body Combinations. R.A.E. Report No. Aero 2590, April 1957. R. and M. 3077.Google Scholar
2.Sheppard, L. M. (1957). The Wave Drag of Non-Lifting Combinations of Thin Wings and “ Non-Slender ” Bodies. R.A.E. Tech. Note No. Aero 2496, March 1957. R. and M. 3076.Google Scholar
3.Young, A. D. (1956). Note on the Wave Drags of Untapered Wings with Streamwise Tips at Zero Lift. The Aeronautical Quarterly, Vol. , Part 3, August 1956.Google Scholar
4.Lock, R. C. An Extension of the Linearised Theory of Supersonic Flow Past Quasi-Cylindrical Bodies, with Application to Wing Body Interference. A.R.C. to be issued.Google Scholar
5.Nielsen, J. N. (1947). Effect of Aspect Ratio on Taper on the Pressure Drag at Supersonic Speeds of Unswept Wings at Zero Lift. N.A.C.A. Tech. Note No. 1487, Nov. 1947.Google Scholar
6.Harmon, S. M. (1947). Theoretical Supersonic Wave Drag of Untapered Swept-back and Rectangular Wings at Zero Lift. N.A.C.A. Tech. Note No. 1449, October 1947.Google Scholar