Hostname: page-component-586b7cd67f-2plfb Total loading time: 0 Render date: 2024-11-28T06:26:40.263Z Has data issue: false hasContentIssue false

Heat Transfer in a Laminar Boundary Layer with Constant Fluid Properties and Constant Wall Temperature

Published online by Cambridge University Press:  04 July 2016

A. G. Smith
Affiliation:
Imperial College of Science and Technology, London S.W.I
D. B. Spalding
Affiliation:
Imperial College of Science and Technology, London S.W.I

Extract

A simple method is given for the calculation of the heat transfer from a laminar flow surface. Computation is by a quadrature. The method is essentially a simplification and extension of the Eckert(1) method, and is applicable both to two–dimensional and to axisymmetric flows.

Type
Technical Notes
Copyright
Copyright © Royal Aeronautical Society 1958

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.Eckert, E. R. G. (1942). Die Berechnung des Wärmeübergangs in der lamineren Grenzschicht umströmter Körper. V.D.I. Forschungsheft 416, 1942.Google Scholar
2.Seban, R. A. (1950). Calculation Method for Two Dimensional Laminar Boundary Layers with Arbitrary Free Stream, Velocity Variation and Arbitrary Wall Temperature Variation. University of California. Institute of Engineering Research Report 2-12, 1950.Google Scholar
3.Drake, R. M. (1953). Calculation Method for Three Dimensional Rotationally Symmetrical Laminar Boundary Layers with Arbitrary Free-Stream Velocity and Arbitrary Wall Temperature Variation. Journal of the Aeronautical Sciences, 20, 5, p. 309, 1953.Google Scholar
4.Squire, H. B. (1942). Heat Transfer Calculation for Aerofoils, R. & M. 1986, 1942.Google Scholar
5.Schuh, H. (1953). A New Method for Calculating Laminar Heat Transfer on Cylinders of Arbitrary Cross-Section and on Bodies of Revolution at Constant and Variable Wall Temperature. K.T.H. Aero T.N. 33, Stockholm, 1953.Google Scholar
6.Lighthill, M. I. (1950). Contributions to the Theory of Heat Transfer Through a Laminar Boundary Layer. Proceedings of the Royal Society A., 202, 359, 1950.Google Scholar
7.Tribus, M. and Klein, J. (1955). Forced Convection Through a Laminar Boundary Over an Arbitrary Surface with an Arbitrary Temperature Variation. Journal of the Aeronautical Sciences, Vol. 22, p. 62, 1955.Google Scholar
8.Walz, A. (1941). Ein neuer Ansatz für das Geschwindigkeitsprofil der laminaren Reibungsschicht. Lilienthal Bericht 141, 8, 1941.Google Scholar
9.Young, A. D. and Winterbottom, N. E. (1942). Note on the Effect of Compressibility on the Profile Drag of Aerofoils in the Absence of Shock Waves. R. & M. 2068, 1942.Google Scholar
10.Thwaites, B. (1949). Approximate Calculation of the Laminar Boundary Layer. Aeronautical Quarterly, Vol. I. p. 245, 1949.Google Scholar
11.Mangler, W. (1948). Zusammenhang zwischen ebenen und rotationssymmetrischen Grenzschichten in Kompressiblen Flussigkeiten. Z.A.M.M., Vol. 28. 1948.Google Scholar