Hostname: page-component-686fd747b7-47r4g Total loading time: 0 Render date: 2025-02-13T11:57:39.620Z Has data issue: false hasContentIssue false
  • English
  • Français

The Slender Wing with a Half Body of Revolution Mounted Beneath

Published online by Cambridge University Press:  04 July 2016

H. Portnoy
H. Portnoy*
Affiliation:
University of Salford
Get access Rights & Permissions [Opens in a new window]

Summary

The slender-body theory of Ward is applied to a configuration consisting of a slender, pointed wing, carrying directly beneath it a pointed half-body of revolution divided along a meridian plane.

Expressions for lift and drag due to incidence are found which are valid in both subsonic and supersonic flow if the flow is attached. The lift result can be used to find pitching moment. For the supersonic case the drag at zero incidence is also found and the expressions for a conical configuration are developed so that a limiting form of these can be compared with the results of ref. 3.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 72 , Issue 693 , September 1968 , pp. 803 - 807
Copyright
Copyright © Royal Aeronautical Society 1968 

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.)

References

1. Ward, G. N. Supersonic Flow Past Slender Pointed Bodies. The Quart J of Mech and App Math, Vol 2, pp 75–97, 1949.Google Scholar
2. Ward, G. N. Linearized Theory of Steady High-Speed Flow, Part 3. Cambridge University Press, 1955.Google Scholar
3. Portnoy, H. The Flow Past a Delta-Wing-Half-Cone Combination with Subsonic Leading Edges. Aero Quart, Vol 15, pp 311–327, 1964.Google Scholar
4. Fraenkel, L. E. and Portnoy, H. Supersonic Flow Past Slender Bodies with Discontinuous Profile Slope. Aero Quart, Vol 6, pp 114–124, 1955.Google Scholar
5. Portnoy, H. The Drag of Ducted Bodies with Annular or Side Intakes in Supersonic Flow. Aero Quart, Vol 10, pp 283–295, 1959.Google Scholar
6. Legendre, R. Écoulement au Voisinage De La Pointe Avant D'une Aile A Forte Fléche Aux Incidences Moy-ennes. La Recherche Aeronautique, No 30, 1952, No 31, 1953 and No 35, 1953.Google Scholar
7. Brown, C. E. and Michael, W. H. Effect of Leading Edge Separation on the Lift of a Delta Wing. J Aero Sciences, Vol 21, pp 690–695 and 706, 1954.Google Scholar
8. Mangler, K. W. and Smith, J. H. B. A Theory of the Flow Past a Slender Delta Wing with Leading Edge Separation. Proc. Roy Soc A, Vol 251, pp 200–217, 1959.Google Scholar
9. Bannink, W. J. and Reyn, J. W. Lift and Drag Calculations on Delta Wing-Cone Configurations having Subsonic Leading Edges using Slender-Body Theory. Tech Univ Delft, Aero Eng Dept Rep VTH-141, 1967.Google Scholar