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A Correlation of Leading Edge Transition and Heat Transfer on Swept Cylinders in Supersonic Flow

Published online by Cambridge University Press:  04 July 2016

D. R. Topham
D. R. Topham*
Affiliation:
Advanced Projects Group, Hawker Siddeley Aviation Ltd.
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Summary:—

It is shown that stagnation line heating rates for laminar, transitional and turbulent boundary layers measured on swept cylinders at supersonic speeds, can be correlated in terms of a Reynolds number based on the spanwise momentum thickness at the stagnation line.

A critical Reynolds number for transition along the stagnation line is determined and experimental results show evidence of transition up to M= 10.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 69 , Issue 649 , January 1965 , pp. 49 - 52
Copyright
Copyright © Royal Aeronautical Society 1965

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References

1.Beckwith, I. E. and Gallagher, J. J. Experimental Investigation of the Effect of Boundary Layer Transition on the Average Heat Transfer to a Yawed Cylinder in Supersonic Flow. NACA/TIL 5160, 1956.Google Scholar
2.Beckwith, I. E. and Gallagher, J. J. Local Heat Transfer and Recovery Temperatures on a Yawed Cylinder at a Mach Number of 4’15 and High Reynolds Numbers. NASA TR R-104, 1961.Google Scholar
3.Chapman, G. T. Some Effects of Leading Edge Sweep on Boundary Layer Transition at Supersonic Speeds. NASA TN D-1075, 1961.Google Scholar
4.Reshotko, E. and Beckwith, I. E. Compressible Laminar Boundary Layer over a Yawed Infinite Cylinder with Heat Transfer and Arbitrary Prandtl Number. NASA Report 1379, 1958.Google Scholar
5.Feller, W. V. Investigation of Equilibrium Temperatures and Average Laminar Heat Transfer Coefficients for the Front Half of Swept Circular Cylinders at a Mach Number of 6-9. NACA/TIB/4789, 1955.Google Scholar
6.Goodwin, G., Creager, M. O. and Winkler, E. L. Investigation of Local Heat Transfer and Pressure Drag Characteristics of a Yawed Circular Cylinder at Supersonic Speeds. NACA/TIL 4945, 1956.Google Scholar
7.Eggers, A. J., Hansen, C. F. and Cunningham|B. E. Theoretical and Experimental Investigation of the Effect of Yaw On Heat Transfer to Circular Cylinders in Hypersonic Flow. NACA/TIB/4749, 1955.Google Scholar
8.Cunningham, B. E. and Kraus, S. Experimental Investigation of the Effect of Yaw on Rates of Heat Transfer to Transverse Circular Cylinders in a 6500 ft/sec Hypersonic Airstream. NACA/TIL/6112, 1958.Google Scholar
9.Bertram, M. H. and Everhard, P. E. An Experimental Study of the Pressure and Heat Transfer Distribution on a 70° Sweep Slab Delta Wing in Hypersonic Flow. NASA TR R-153, 1963.Google Scholar
10.Braslow, A. L. A Review of the Effect of Distributed Surface Roughness on Boundary Layer Transition. AGARD Report 254, 1960.Google Scholar
11.Holloway, P. F. and Sterrett, J. R. Effect of Controlled Surface Roughness on Boundary Layer Transition and Heat Transfer at Mach Numbers of 4-8 and 6. NASA TN D-2054, 1964.Google Scholar
12.Kuethe, A. M., Willmarth, W. W. and Crocker, G. H. Stagnation Point Fluctuations and Boundary Layer Stability for Bodies of Revolution with Hemispherical Noses. AGARD Report 267, 1960.Google Scholar
13.Sutera, S. P., Meader, P. F. and Kestin, J.On the Sensitivity of Heat Transfer in the Stagnation Point Boundary Layer to Freestream Vorticity. Journal of Fluid Mechanics, Vol. 16, Part 4, p. 497, August 1963.CrossRefGoogle Scholar