Hostname: page-component-cd9895bd7-jn8rn Total loading time: 0 Render date: 2024-12-27T14:02:56.496Z Has data issue: false hasContentIssue false
  • English
  • Français

An experimental flow with zero skin friction throughout its region of pressure rise

Published online by Cambridge University Press:  28 March 2006

B. S. Stratford
B. S. Stratford
Affiliation:
National Gas Turbine Establishment, Farnborough
Get access Rights & Permissions [Opens in a new window]

Abstract

A flow has been produced having effectively zero skin friction throughout its region of pressure rise, which extended for a distance of 3 ft. No fundamental difficulty was encountered in establishing the flow and it had, moreover, a good margin of stability. The dynamic head in the zero skin friction boundary layer was found to be linear at the wall (i.e. u ∞ y½), as predicted theoretically in the previous paper (Stratford 1959).

The flow appears to achieve any specified pressure rise in the shortest possible distance and with probably the least possible dissipation of energy for a given initial boundary layer. Thus an aerofoil which could utilize it immediately after transition from laminar flow would be expected to have a very low drag. A design pressure distribution (besides having the usual safety margin against stall) should have a slightly more gradual start to the pressure rise than in the present experiment, as small errors close to the discontinuity can cause difficulty.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 5 , Issue 1 , January 1959 , pp. 17 - 35
Copyright
© 1959 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

Clauser, F. H. 1954 J. Aero. Sci. 21, 91.
Von Doenhoff, A. E. & Tetervin, N. 1943 Rep. Nat. Adv. Comm. Aero., Wash., no. 772.
Eppler, R. 1955 Z. Flugwiss, 3, 345 (British M.o.S. transl., in preparation).
Ludweig, H. & Tillmann, W. 1949 Tech. Mem. Nat. Adv. Comm. Aero., Wash., no. 1285(transl.).
Speidel, L. 1955 Z. Flugwiss, 3, 353 (British M.o.S. transl., in preparation).
Squire, H. B. 1950 Rep. & Mem. Aero. Res. Coun., Lond., no. 2751.
Stratford, B. S. 1956 Curr. Pap. Aero. Res. Coun., Lond., no. 307.
Stratford, B. S. 1959 J. Fluid Mech. 5, 1.
Truckenbrodt, E. 1952 Ingen.-Arch. 20, 211.
Wortmann, F. X. 1955 Z. Flugwiss, 3, 333 (British M.o.S. transl., in preparation).
Wortmann, F. X. 1957 Z. Flugwiss, 5, 228 (British M.o.S. transl., in preparation).