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The Behaviour and Effects of Laminar Separation Bubbles on Aerofoils in Incompressible Flow*

Published online by Cambridge University Press:  04 July 2016

Julian W. Ward
Julian W. Ward*
Affiliation:
Hatfield Branch
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Summary

A survey of information on laminar separation bubbles and their effect on the stalling characteristics of aerofoils is presented. It is shown that there are two principal kinds of bubbles and that their existence can be predicted. It is believed that their behaviour may be related to the kind of boundary layer transition process present.

It is intended that a second part of this paper will describe the characteristics of aerofoils at Reynolds numbers typical of model aircraft and show how the observed phenomena are related to the behaviour of laminar separation bubbles.

Type
Research Article
Information
The Aeronautical Journal , Volume 67 , Issue 636 , December 1963 , pp. 783 - 790
Copyright
Copyright © Royal Aeronautical Society 1963

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Footnotes

*

21-26 Years of Age Group.

References

1.Jones, B. M. An Experimental Study of the Stalling of Wings. R & M 1588, December 1933.Google Scholar
2.Jones, B. M. Stalling. Journal of the Royal Aeronautical Society, Vol. 38, pp. 753–770, September 1934.Google Scholar
3.Von Doenhoff, A. E. A Preliminary Investigation of Boundary Layer Transition Along a Flat Plate with Adverse Pressure Gradient. NACA Tech. Note No. 693, 1938.Google Scholar
4.Tani, I.Note on the Interplay Between Laminar Separation and the Transition from Laminar to Turbulent of the Boundary Layer. J Soc. Aero. Sci. Japan, Vol. 6, pp. 122–134 (in Japanese), 1939.Google Scholar
5.Von Doenhoff, A. E. and Tetervin, N. Investigation of the Variation of Lift Coefficient with Reynolds Number at a Moderate Angle of Attack on a Low-Drag Airfoil. NACA Wartime Rep. L-661; NACA/TIB/315, November 1942.Google Scholar
6.Curle, N. and Skan, S. W.Approximate Methods for Predicting Separation Properties of Laminar Boundary Layers. Aeronautical Quarterly, Vol. VIII, Part III, August 1957.Google Scholar
7.Gault, D. E. Boundary Layer and Stalling Characteristics of the NACA 63-009 Airfoil Section. NACA Tech. Note 1894, June 1949.Google Scholar
8.McCullough, G. B. and Gault, D. E. Boundary Layer and Stalling Characteristics of the NACA 64AO06 Airfoil Section. NACA Tech. Note 1923, August 1949.Google Scholar
9.Peterson, R. F. The Boundary Layer and Stalling Characteristics of the NACA 64A010 Airfoil Section. NACA Tech. Note 2235, November 1950.Google Scholar
10.Bursnall, W. J. and Loftin, L. K. Jr. Experimental Investigation of Localised Regions of Laminar-Boundary-Layer Separation. NACA Tech. Note 2338, April 1951.Google Scholar
11.McCullough, G. B. and Gault, D. E. Examples of Three Representative Types of Airfoil-Section Stall at Low Speed. NACA Tech. Note 2502, September 1951.Google Scholar
12.Maekawa, T. and Atsumi, S.Transition Caused by the Laminar Flow Separation. J Soc. App. Mech. Japan, Vol. 1, No. 6, Nov. 1948; NACA Tech. Memo. 1352, Sept. 1952.Google Scholar
13.Hurley, D. G. and Ward, G. F. Experiments on the Effects of Air Jets and Surface Roughness on the Boundary Layer Near the Nose of an NACA 64A0O6 Aerofoil. Aero. Res. Lab. Aero. Note 128 (Australia), 1953.Google Scholar
14.Owen, P. R. and Klanfer, L. On the Laminar Boundary Layer Separation from the Leading Edge of a Thin Aerofoil. RAE Rep. Aero. 2508, October 1953.Google Scholar
15.Woods, L. C. Theory of Aerofoils on which Occur Bubbles of Stationary Air. ARC 16 277, November 1953; R & M 3049, 1957.Google Scholar
16.Black, J. and Hunt, R. D.Some Measurements of Leading Edge Separation Bubbles on a 10 per cent Thick Symmetrical Aerofoil. Journal Royal Aeronautical Society, Dec. 1953.Google Scholar
17.Levey, H. C. The Effect of a Small Protuberance on the Potential Flow Past an Airfoil. Aero. Res. Lab. Note ARL/A.134, lune 1954.Google Scholar
18.McGregor, I.Regions of Localised Boundary Layer Separation and Their Role in the Nose Stalling of Aerofoils. Ph.D. Thesis, Queen Mary College, London, June 1954.Google Scholar
19.Wallis, R. A. Experiments With Air Jets to Control the Nose Stall on a 3 ft. Chord NACA 64AO06 Aerofoil. Aero. Res. Lab. Aero Note 139, September 1954.Google Scholar
20.Crabtree, L. F. The Formation of Regions of Separated Flow on Wing Surfaces. Part I. Low Speed Tests on a Two Dimensional Unswept Wing With a 10% Thick RAE 101 Section. RAE Rep. Aero 2528, November 1954; R & M 3122, 1959.Google Scholar
21.Hurley, D. G. The Downstream Effect of a Local Thickening of the Laminar Boundary Layer. Aero. Res. Lab. Aero Note 146, 1955.Google Scholar
22.Norbury, J. F. and Crabtree, L. F. A Simplified Model of the Incompressible Flow Past Two-Dimensional Aerofoils With a Long Bubble Type of Flow Separation. RAE Tech. Note Aero 2352, June 1955.Google Scholar
23.Schubauer, G. B. and Klebanoff, P. S. Contributions on the Mechanics of Boundary Layer Transition. NACA Tech. Note No. 3489, September 1955.Google Scholar
24.Gault, D. E. An Experimental Investigation of Regions of Separated Laminar Flow. NACA Tech. Note No. 3505, September 1955.Google Scholar
25.Lochtenbero, B. H. Some Studies of Transition in a Laminar Boundary Layer After Separation. ARC 17 972, Oct. 1955.Google Scholar
26.McCullough, G. B. The Effects of Reynolds Number on the Stalling Characteristics and Pressure Distributions of Four Moderately Thin Airfoil Sections. NACA Tech. Note No. 3524, November 1955.Google Scholar
27.Crabtree, L. F. and Weber, J. Some Effects of Flow Separations on Thin Wings With Unswept Leading Edges. RAE Tech. Note Aero 2403, October 1955.Google Scholar
28.Maskell, E. C. A Theoretical Treatment of the Thin- Aerofoil Stall. Unpublished RAE Report.Google Scholar
29.Maskell, E. C. Wake Circulation and Its Influence on Lift in Two-Dimensional Compressible Flow. Unpublished RAE Report.Google Scholar
30.Maki, R. L. and Hunton, L. W. An Investigation at Sub sonic Speeds of Several Modifications to the Leading Edge Region of the NACA 64A010 Airfoil Section Designed to Increase Maximum Lift. NACA Tech. Note 3871, 1956.Google Scholar
31.Gault, D. E. An Investigation at Low Speed of the Flow Over a Simulated Flat Plate at Small Angles of Attack Using Pitot-Static and Hot-Wire Probes. NACA Tech. Note 3876, March 1957.Google Scholar
32.Gault, D. E. A Correlation of Low-Speed, Airfoil-Section Stalling Characteristics With Reynolds Number and Airfoil Geometry. NACA Tech. Note 3963, March 1957.Google Scholar
33.Wallis, R. A. and Ruglen, N. Note on the Breakdown of the Laminar Separation Bubble on the Nose of a Thin Wing. Aero. Res. Lab. Aero Note 161, 1957.Google Scholar
34.Hurley, D. G. and Ruglen, N. A Note on the Cause of the Nose Stall of Thin Wings. Aero. Res. Lab. Aero. Note 162, 1957.Google Scholar
35.Crabtree, L. F. The Formation of Regions of Separated Flow on Wing Surfaces. Part II. Laminar Separation Bubbles and the Mechanism of Leading Edge Stall. RAE Rep. Aero. 2578, July 1957; R & M 3122, 1959.Google Scholar
36.Crabtree, L. F.Effects of Leading Edge Separation on Thin Wings in Two-Dimensional Incompressible Flow. Journ. Aero. Sci., Vol. 24, No. 8, pp. 597–604, August 1957.Google Scholar
37.Crabtree, L. F.Prediction of Transition in the Boundary Laver on an Aerofoil. Journal of the Royal Aeronautical Society, Vol. 62, pp. 525–527, July 1958.Google Scholar
38.Evans, W. T. and Mort, K. W. An Analysis of Computed Flow Parameters for a Set of Sudden Stalls in Low-Speed Two-Dimensional Flow. NASA Tech. Note D.85, Aug. 1959.Google Scholar
39.Moore, T. W. F.A Note on the Causes of Thin Aerofoil Stall. Journal of the Royal Aeronautical Society, Vol. 63, pp. 724–730, December 1959. Google Scholar
40.Lochtenberg, B. H.Transition in a Separated Laminar Boundary Layer. Journal Aerospace Sci., Vol. 27, No. 2, February 1960.Google Scholar
41.Woodward, D. S.An Investigation of Boundary Layer Behaviour at Chordwise Reynolds Numbers of the Order of 100,000, With Special Reference to Aerofoil Performance in the Reynolds Number Range 21,000 to 170,000. B.Sc.(Eng.) Part III Thesis, Queen Mary College, London, June 1960.Google Scholar
42.Wallis, R. A. Boundary Laver Transition at the Leading Edge of Thin Wings and its Effect on General Nose Separation. ICAS Second Congress, Zurich, Sept. 1960.Google Scholar
43Savage, S. B.An Approximate Analysis for Re-attaching Turbulent Shear Layers in Two-Dimensional Incomrjressible Flow. Mech. Eng. Res. Lab., McGill University, Montreal, Rep. Aero. 3, 1960.Google Scholar
44.Tani, I. Critical Survey of Published Theories on the Mechanism of Leading Edge Stall. Aero. Res. Inst. University of Tokyo, Rep. No. 367, June 1961; ARC 23428, Pert. 2063, January 1962.Google Scholar
45.Gaster, M. Private communication to author, 1962.Google Scholar
46.Moore, T. W. F.Some Experiments on the Reattachment of a Laminar Boundary Layer Separating from a Rearward Facing Step on a Flat Plate Aerofoil. Journal of the Royal Aeronautical Society, Vol. 64, pp. 668–672, November 1960.Google Scholar