Hostname: page-component-78c5997874-m6dg7 Total loading time: 0 Render date: 2024-11-15T02:28:32.811Z Has data issue: false hasContentIssue false
  • English
  • Français

Methods of Reducing the Transonic Drag of Swept - Back Wings at Zero Lift*

Published online by Cambridge University Press:  28 July 2016

D. Küchemann
D. Küchemann*
Affiliation:
Royal Aircraft Establishment, Farnborough
Get access Rights & Permissions [Opens in a new window]

Extract

The purpose of this paper is to review briefly some means of reducing the normal-pressure drag at transonic speeds of wings and wing-body combinations without lift. By transonic speeds is meant here not only the range of main stream Mach numbers around unity but, more generally, that speed range where a transonic type of flow around the body may exist. Thick non-lifting bodies as are considered here cause a displacement flow and it may be recalled that at least three different types of flow are involved: a subsonic, a transonic, and a supersonic type of flow, all of which are here assumed to have one attachment line along the leading edge and one separation line along the trailing edge. This excludes types of flow where separations occur elsewhere, such as shock-induced separations along some line within the wing chord.

Type
Research Article
Information
The Aeronautical Journal , Volume 61 , Issue 553 , January 1957 , pp. 37 - 42
Copyright
Copyright © Royal Aeronautical Society 1957

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

Footnotes

*

This paper was given at the Ninth International Congress of Applied Mechanics, Brussels in 1956. Only a short abstract will be published in the Congress Proceedings.

References

1. Küchemann, D. and Weber, J. (1953). The Subsonic Flow Past Swept Wings at Zero Lift Without and With Body. A.R.C. R. & M. 2908, March 1953.Google Scholar
2. Warren, C. H. E. (1956). Recent Advances in the Knowledge of Transonic Air Flows. Journal of the Royal Aeronautical Society, Vol. 60, p. 241, April 1956.CrossRefGoogle Scholar
3. Küchemann, D. and Hartley, D. E. (1955). The Design of Swept Wings and Wing-Body Combinations to have Low Drag at Transonic Speeds. Unpublished M.O.S. Report, April 1955.Google Scholar
4. Holder, D. W., Pearcy, H. H. and Gadd, G. E. (1954). The Interaction Between Shock Waves and Boundary Layers. Unpublished M.O.S. Report, February 1954.Google Scholar
5. Holder, D. W. (1955). The Interaction Between Shock Waves and Boundary Layers. Proceedings of the Fifth Anglo-American International Aeronautical Conference, Los Angeles, 1955. Institute of the Aeronautical Sciences.Google Scholar
6. Whitcomb, R. T. (1955). A Study of the Zero-Lift Drag- Rise Characteristics of Wing-Body Combinations Near the Speed of Sound. N.A.C.A. R.M. L52H08, September 1952, see also: N.A.C.A. details area rule breakthrough. Aviation Week, Vol. 63, p. 28, 19th September 1955.Google Scholar
7. Haines, A. B. (1956). Wing Section Design for Sweptback Wings at Transonic Speeds. Paper presented at the IX International Congress of Applied Mechanics, Brussels, 1956. To he published in the Journal of the Royal Aeronautical Society.Google Scholar
8. Graham, E. W., Beane, B. J. and Licher, R. M. (1955). The Drag of Non-Planar Thickness Distributions in Supersonic Flow. The Aeronautical Quarterly, Vol, 6, p. 99, May 1955.CrossRefGoogle Scholar
9. Betz, A. (1940). Sonderaufgaben der Aerodynamischen Forschung. Schriften der Deutschen Akademie der Luftfahrtforschung, 1940.Google Scholar
10. Küchemann, D. and Weber, J. (1953). Aerodynamics of Propulsion. McGraw-Hill Book Co., New York and London, 1953.Google Scholar
11. Hilton, W. F. (1955). Tests of a Fairing to Reduce the Drag of a Supersonic Swept-Wing Root. Journal of the Aeronautical Sciences, Vol. 22, p. 173, March 1955.CrossRefGoogle Scholar
12. McDevitt, J. B. and Haire, W. M. (1956). Investigation at High Subsonic Speeds of a Body-Contouring Method for Alleviating the Adverse Interference at the Root of a Swept-back Wing. N.A.C.A. T.N. 3672, April 1956.Google Scholar