Hostname: page-component-cd9895bd7-gvvz8 Total loading time: 0 Render date: 2024-12-29T13:44:04.628Z Has data issue: false hasContentIssue false
  • English
  • Français

Boundary-layer drag in three-dimensional supersonic flow

Published online by Cambridge University Press:  28 March 2006

J. C. Cooke
J. C. Cooke
Affiliation:
Royal Aircraft Establishment, Farnborough
Get access Rights & Permissions [Opens in a new window]

Abstract

A general theorem for drag is given according to which the boundary-layer drag of a body is equal to the inviscid drag of the displacement surface together with a term which is given as an integral involving the ‘streamwise’ momentum and displacement thicknesses taken round the trailing edge. A less accurate result for thin slender wings is that the boundary-layer drag is equal to the line integral $\rho _\infty U^2_\infty \int \Theta d \sigma$ taken round the trailing edge, where Θ is the streamwise momentum thickness. This result leads to the possibility of finding boundary-layer drag by means of a traverse round the trailing edge. The extension of the results to wings with swept trailing edges is also given.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 17 , Issue 1 , September 1963 , pp. 61 - 74
Copyright
© 1963 Cambridge University Press

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

Cooke, J. C. 1961 A calculation method for three-dimensional turbulent boundary layers. Aero. Res. Coun., Lond., Rep. & Mem. no. 3199.Google Scholar
Howarth, L. 1953 (ed). Modern Developments in Fluid Dynamics. High-speed flow. Oxford University Press.
Lighthill, M. J. 1956 The wave drag at zero lift of slender delta wings and similar configurations. J. Fluid Mech. 1, 337.Google Scholar
Lighthill, M. J. 1958 On displacement thickness. J. Fluid Mech. 4, 383.Google Scholar
Meyer, R. E. 1957 On the measurement of supersonic aerofoil drag by pressure traverse. Aero. Quart. 8, 123.Google Scholar
Spence, D. A. 1954 Prediction of the characteristics of two-dimensional aerofoils. J. Aero. Sci. 21, 577.Google Scholar
Squire, H. B. & Young, A. D. 1938 The calculation of the profile drag of aerofoils. Aero. Res. Coun., Lond., Rep. & Mem. no. 1838.Google Scholar
Ward, G. N. 1949 Supersonic flow past slender pointed bodies. Quart. J. Mech. Appl. Math. 2, 75.Google Scholar
Weber, J. 1957 Slender delta wings with sharp edges at zero lift. Unpublished M. O. A. Report. Aero. Res. Coun. no. 19,549.Google Scholar
Weber, J. 1960 The effect of the geometry near the trailing edge on the zero lift wave drag of slender wings. Unpublished M. O. A. Report. Aero. Res. Coun. no. 22,147.Google Scholar
Young, A. D. 1953 The calculation of the profile drag of aerofoils and bodies of revolution at supersonic speeds. Coll. Aero. Rep. no. 73, Aero. Res. Coun. no. 15,970.Google Scholar
Young, A. D. & Kirkby, S. 1955 The profile drag of bi-convex and double wedge sections at supersonic speeds. Proceedings of a symposium on boundary layer effects in aerodynamics held at the Nat. Phys. Lab., London.