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Some observations of the transition process on the windward face of a long yawed cylinder

Published online by Cambridge University Press:  20 April 2006

D. I. A. Poll
Affiliation:
Aerodynamics Division, College of Aeronautics, Cranfield Institute of Technology

Abstract

An experiment has been performed to determine the effect of yaw upon transition in the boundary layer formed on the windward face of a long cylinder. The china-clay-evaporation and surface-oil-flow techniques have been used to study the development of the fixed-wavelength stationary disturbances which are characteristic of cross-flow instability. It has been found that the boundary layer is also susceptible to time-dependent disturbances which grow to very large amplitudes prior to the onset of transition. These disturbances have been studied with a hot-wire anemometer. The conditions necessary for the onset and completion of transition have been determined by the use of surface Pitot tubes. Data from the experiment have been compared with the simple criteria for instability and transition which were proposed by Owen & Randall over thirty years ago. In general it has been found that these criteria are inadequate, and, where possible, improvements have been proposed. The raw data are presented in sufficient detail for them to be used to test, or calibrate, future theoretical models of the transition process in three-dimensional boundary-layer flows.

Type
Research Article
Copyright
© 1985 Cambridge University Press

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References

Allen, L. D. & Burrows F. M.1956 Flight experiments on the boundary layer characteristics of a swept back wing. Coll. Aero. Rep. 104, Cranfield Inst. Tech.Google Scholar
Anscombe, A. & Illingworth L. N.1952 Wind-tunnel observations of boundary layer transition on a wing at various angles of sweep back. ARC R & M 2968.
Arnal D.1982 (April) Private Communication, 10th Meeting of the Eurovisc Working Party on Boundary Layer Transition, Cranfield Institute of Technology.
Beasley J. A.1973 Calculation of the laminar boundary layer and prediction of transition on a sheared wing. ARC R & M 3787.Google Scholar
Boltz F. W., Kenyon, G. C. & Allen C. Q.1960 Effects of sweep angle on the boundary layer stability characteristics of an untapered wing at low speeds. NASA TN D-338.Google Scholar
Brown W. B.1961 A stability criterion for three-dimensional laminar boundary layers. In Boundary Layer and Flow Control (ed. G. V. Lachman), vol. 2, pp. 913923. Pergamon.
Burrows F. M.1956 A theoretical and experimental study of the boundary layer flow on a 45 swept back wing. Coll. Aero. Rep. 109, Cranfield Inst. Tech.Google Scholar
Coustols E.1983 Stabilité et transition en écoulement tridimensionnel: Cas des ailes en flèche. Thesis, L'Ecole Nationale Supérieure de l'Aéronautique et de l'Espace, Toulouse.
Cumpsty N. A.1977 (April) Private communication, Whittle Laboratory, Cambridge University Engineering Department.
Cumpsty, N. A. & Head M. R.1969 The calculation of the three-dimensional turbulent boundary layer. Part III. Comparison of attachment line calculations with experiment. Aero. Q. 20, 99113.Google Scholar
Edwards J. B.1977 Laminar flow control - concepts, experiences, speculations. Paper 4, Special Course on Concepts for Drag Reduction; AGARD Rep. 654.Google Scholar
Gaster M.1967 On the flow along swept leading edges. Aero. Q. 18, 165184.Google Scholar
Gray W. E.1952a The effect of wing sweep on laminar flow. RAE TM Aero 255.Google Scholar
Gray W. E.1952b The nature of the boundary layer flow at the nose of a swept wing. RAE TM Aero 256.Google Scholar
Gregory N., Stuart, J. T. & Walker W. S.1955 On the stability of three-dimensional boundary layers with application to the flow due to a rotating disc Phil. Trans. R. Soc. Lond. A 248, 155199.Google Scholar
Hall P., Malik, M. R. & Poll D. I. A.1984 On the stability of an infinite swept attachment-line boundary layer Proc. R. Soc. Lond. A 395, 229245.Google Scholar
Jones R. T.1947 Effects of sweepback on boundary layer and separation. NACA Rep. 884.Google Scholar
Klebanoff P. S., Tidstrom, K. D. & Sargent L. M.1962 The three-dimensional nature of boundary-layer instability. J. Fluid Mech. 12, 134.Google Scholar
Kuethe A. M.1950 Some aspects of boundary-layer transition and flow separation on cylinders in yaw. Proc. 1st Mid-Western Conf. Fluid Dynamics, Ann Arbor, Michigan.
Lachmann, G. V. (ed.) 1961 Boundary Layer and Flow Control, vols I and II. Pergamon.
Maltby, R. L. & Keating R. F. A.1962 The surface oil flow technique for use in low speed wind tunnels. AGAR Dograph 70.Google Scholar
Owen, P. R. & Randall D. G.1952 Boundary layer transition on a sweptback wing. RAE TM Aero 277.Google Scholar
Owen, P. R. & Randall D. G.1953 Boundary layer transition on a sweptback wing: a further investigation. RAE TM Aero 330.Google Scholar
Pfenninger W.1977 Laminar flow control, laminarization. Paper 3, Special Course on Concepts for Drag Reduction, AGARD Rep. 654.Google Scholar
Poll D. I. A.1979 Transition in the infinite swept attachment-line boundary layer. Aero. Q. 30, 607628.Google Scholar
Richards, E. J. & Burstall F. H.1945 The china clay method of indicating transition position. ARC R & M 2126.Google Scholar
Rosenhead, L. (ed.) 1963 Laminar Boundary Layers. Oxford University Press.
Saric, W. S. & Thomas A. S. W.1983 Experiments on the subharmonic route to turbulence in boundary layers. Proc. IUTAM Symp. on Turbulence and Chaotic Phenomena in Fluids, Kyoto.
Schlichting H.1933 Zur Entstehung der Turbulenz bei der Plattenströmung. Nachr. Ges. Wiss. Gött. Math. Phys. Kl., 182208.
Schubauer, G. B. & Skramstad H. K.1947 Laminar boundary layer oscillations and stability of laminar flow. J. Aero. Sci. 14, 6978.Google Scholar
Sears W. R.1948 The boundary layer of yawed cylinders. J. Aero. Sci. 15, 2834.Google Scholar
Stuart J. T.1952 An interim note on the stability of the boundary layer on a swept wing. ARC 14, 991.Google Scholar
Squire H. B.1933 On the stability of three-dimensional disturbances of viscous fluid flow between parallel walls Proc. R. Soc. Lond. A 142, 621628.Google Scholar
Squire H. B.1952 Addendum on sweepback and transition, to RAE TM Aero 277.
Tollmien W.1931 On the production of turbulence. NACA TM 609.Google Scholar
Wazzan A. R., Gazley, C. & Smith A. M. O.1982 H-Rx method for predicting transition. AIAA J. 19, 810812.Google Scholar