Hostname: page-component-78c5997874-xbtfd Total loading time: 0 Render date: 2024-11-02T18:42:23.613Z Has data issue: false hasContentIssue false
  • English
  • Français

The Estimation of the Non-Linear Lift of Delta Wings at Supersonic Speeds

Published online by Cambridge University Press:  04 July 2016

L. C. Squire
L. C. Squire*
Affiliation:
Department of Aeronautical Engineering, Queen's University, Belfast
Get access Rights & Permissions [Opens in a new window]

Summary:

Up to the present most of the methods used to calculate the flow over delta wings with leading edge separations have been based on slender wing theory. In this paper one of the simplest of these methods is carried over to linear theory and the overall lift calculated. In general the results are in agreement with experiment, in particular both show a fall in nonlinear lift as the leading edges of the wing approach the free stream Mach angles. The discrepancies which exist appear to arise mainly from the use of linear theory rather than from the mathematical model introduced to treat the separated flow.

Type
Research Article
Information
The Aeronautical Journal , Volume 67 , Issue 632 , August 1963 , pp. 476 - 480
Copyright
Copyright © Royal Aeronautical Society 1963

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.Stanbrook, A. and Squire, L. C. Possible Types of Flow at Swept Leading Edges. Unpublished M of A Report.Google Scholar
2.Kuchemann, D. A Non-Linear Lifting Surface Theory for Wings of Small Aspect Ratio with Edge Separations. Un published M of A Report.Google Scholar
3.Squire, L. C., Jones, J. G. and Stanbrook, A. An Experimental Investigation of the Characteristics of Some Plane and Cambered 65° Delta Wings at Mach Numbers from 0·7 to 2·0. R and M 3305, July 1961.Google Scholar
4.Mangler, K. and Smith, J. H. B.A Theory of the Flow Past a Slender Delta Wing with Leading Edge Separations. Proc. Roy. Soc., Vol. 251, pp. 200–217, 1959.Google Scholar
5.Thwaites, B. (editor). Incompressible Aerodynamics. O.U.P.Google Scholar
6.Bolton-Shaw, B. W. Nose Controls on Delta Wings at Supersonic Speeds. College of Aeronautics Report No. 36, May 1950.Google Scholar
7.Squire, L. C. Pressure Distributions and Flow Pattern on Some Conical Shapes with Sharp Edges and Symmetrical Cross-sections at M =4·0. To be issued in the R and M series.Google Scholar
8.Michael, W. H. Flow Studies on Flat-Plate Delta Wings at Supersonic Speeds. N.A.C.A. Tech. Note 3472, July 1955.Google Scholar