Hostname: page-component-848d4c4894-pjpqr Total loading time: 0 Render date: 2024-07-05T03:14:19.583Z Has data issue: false hasContentIssue false
  • English
  • Français

Some Measurements of Leading Edge Separation Bubbles on a 10 per cent Thick Symmetrical Aerofoil

Published online by Cambridge University Press:  28 July 2016

J. Black  and
R. D. Hunt
J. Black
Affiliation:
University of Bristol, Department of Aeronautical Engineering
R. D. Hunt
Affiliation:
University of Bristol, Department of Aeronautical Engineering
Get access Rights & Permissions [Opens in a new window]

Extract

Pressure Distribution and liquid-film tests on a 10 per cent, thick aerofoil revealed the presence of separation “bubbles” close to the leading edge. These bubbles are formed beneath the boundary layer which separates near the leading edge and re-attaches farther aft; their existence is usually indicated by localised constant-pressure regions in the pressure distributions. It is also believed that if a thin film of liquid (such as a suspension of lamp-black in paraffin) is spread on the surface, the scrubbing action of the air rotating in the bubble will tend to draw liquid forward into the bubble, and hence the location and extent of the bubble may be indicated approximately by the accumulation of the fluid.

Many boundary layer traverses of bubbles on N.A.C.A. aerofoils have been made, but it was felt that similar measurements of the bubbles on this particular aerofoil would provide useful data, since the separation characteristics of this section appeared to differ from those in the N.A.C.A. tests.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 57 , Issue 516 , December 1953 , pp. 819 - 823
Copyright
Copyright © Royal Aeronautical Society 1953

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. Black, J. (1953). Pressure Distribution and Boundary Layer Investigations on a 44° Sweptback Wing. Part I I: Two-Dimensional Pressure Distribution Tests on a 10 per cent. Thick Symmetrical Aerofoil Section. A.R.C. Current Paper No. 137 (to be published).Google Scholar
2. Gault, D. E. (1949). Boundary Layer and Stalling Characteristics of the N.A.C.A. 63-009 Airfoil Section. N.A.C.A. T.N. 1894, June 1949.Google Scholar
3. McCullough, G. B. and Gault, D. E. (1949). Boundary Layer and Stalling Characteristics of the N.A.C.A. 64 A. 006 Airfoil Section. N.A.C.A. T.N. 1923, August 1949.Google Scholar
4. Bursnall, W. J. and Loftin, L. K. (1951). Experimental Investigation of Localised Regions of Laminar Boundary Layer Separation. N.A.C.A. T.N. 2338, April 1951.Google Scholar
5. McCullough, G. B. and Gault, D. E. (1951). Examples of Three Representative Types of Airfoil Section Stall at Low Speed. N.A.C.A. T.N. 2502, September 1951.Google Scholar