Hostname: page-component-cd9895bd7-mkpzs Total loading time: 0 Render date: 2024-12-25T17:35:32.961Z Has data issue: false hasContentIssue false
  • English
  • Français

The Design of Wing Plan Forms for Transonic Speeds

Published online by Cambridge University Press:  07 June 2016

R. C. Lock
R. C. Lock*
Affiliation:
Aerodynamics Division, National Physical Laboratory
Get access

Summary

A method is suggested for designing the shape of the plan form of an unwarped swept-back wing so as to control the magnitude of the singularity that occurs in the chordwise loading distribution at the leading edge. At a Mach number of unity it is possible to do this simply and directly by an approximate application of linearised lifting-surface theory. Details are given of three families of wing plan forms, of varying sweep and aspect ratio, in all of which the strength of the leading-edge singularity is held constant near the wing tips, behind the Mach line from the root trailing edge. The local chordwise load distributions have been calculated in detail for several of these wings and it is found that in all cases the loading curves become effectively independent of spanwise position over that part of the span for which the singularity is constant.

Type
Research Article
Information
Aeronautical Quarterly , Volume 12 , Issue 1 , February 1961 , pp. 65 - 93
Copyright
Copyright © Royal Aeronautical Society. 1961

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. Jones, R. T. and Doris, Cohen. Aerodynamic Components of Aircraft at High Speeds: Section A, Chapters 2 and 3. (Vol. VII of High Speed Aerodynamics and Jet Propulsion, edited by Donovan, A. F. and Lawrence, H. R.). Princeton, 1957.Google Scholar
2. Mangler, K. W. Calculation of the Pressure Distribution over a Wing at Sonic Speeds. R.&M. 2888, 1951.Google Scholar
3. Mirels, H. Aerodynamics of Slender Wings and Wing-Body Combinations having Swept Trailing Edges. N.A.C.A. T.N. 3105, 1954.Google Scholar
4. Hall, I. M. and Rogers, E. W. E. Experiments on a Tapered Swept-Back Wing (Warren 12) at Mach Numbers between 0·6 and 1·6. A.R.C. 22,050. To be published in the R. & M. series.Google Scholar
5. Brebner, G. G. The Design of Swept Wing Plan Forms to Improve Tip Stalling Characteristics. A.R.C. 17,264, July 1954.Google Scholar