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Hypersonic Laminar Heat Transfer and Boundary Layer Transition on Blunted Cones

Published online by Cambridge University Press:  07 June 2016

N. B. Wood
N. B. Wood*
Affiliation:
Royal Armament Research and Development Establishment
*
*Present address: Physiological Flow Studies Unit, Imperial College of Science and Technology.
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Summary

Measurements have been made of laminar and transitional heat transfer rate distribution on a 15° semi-vertex angle, spherically blunted, cone at Mach numbers 8·6, 10·6 and 13·0. The laminar results are compared with theoretical predictions and good agreement is obtained with a modified form of the analysis due to Lees. Using a development of the correlation of pressure distributions previously obtained by the author, a new correlation of experimental and theoretical heat transfer results is suggested. The effect of nose bluntness on boundary layer transition has been observed both from flow visualisation and heat transfer results. It is suggested that the main factor causing nose bluntness to influence transition is the adverse pressure gradient which is induced.

Type
Research Article
Information
Aeronautical Quarterly , Volume 19 , Issue 4 , November 1968 , pp. 301 - 316
Copyright
Copyright © Royal Aeronautical Society. 1968

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References

1. Wood, N. B. Nose bluntness effects on cone pressure and shock shape at M = 8·5 to 12·9. AlAA Journal, Vol. 1, No. 8, p. 1929, 1963.Google Scholar
2. Lees, L. Laminar heat transfer over blunt-nosed bodies at hypersonic flight speeds. Jet Propulsion, Vol. 26, No. 4, pp. 259-269, 1956.CrossRefGoogle Scholar
3. Cheng, H. K. Hypersonic flow with combined leading-edge bluntnesss and boundary layer displacement effect. Cornell Aeronautical Laboratory Report AF-1285-A-4, August 1960.CrossRefGoogle Scholar
4. Wittliff, C. E. and Wilson, M. R. Heat transfer to slender cones in hypersonic air flow including yaw and nose-bluntness effects. Institute of the Aerospace Sciences/American Rocket Society Paper 61-213-1907, June 1961.Google Scholar
5. Griffith, B. J. and Lewis, C. H. Laminar heat transfer to spherically blunted cones at hypersonic conditions. AlAA Journal, Vol. 2, No. 3, p. 438, 1964.Google Scholar
6. Wilkinson, D. B. and Harrington, S. A. Hypersonic force, pressure and heat transfer investigations of sharp and blunt slender cones. Cornell Aeronautical Laboratory Report AF-1560-A-5, 1962.Google Scholar
7. Sanator, R. J., de Carlo, J. P. and Torrillo, D. T. Hypersonic boundary-layer transition data for a cold-wall slender cone. AlAA Journal, Vol 3, No. 4, p. 758, 1965.Google Scholar
8. Daum, F. L. Air condensation in a hypersonic wind tunnel. AlAA Journal, Vol. 1, No. 5, p. 1043, 1963.Google Scholar
9. Sykes, D. M. and Winter, D. F. T. Unpublished British War Office Memorandum.Google Scholar
10. Conti, R. J. Approximate temperature distributions and streamwise heat conduction effects in the transient aerodynamic heating of thin-skinned bodies. NASA TN D-895, September 1961.Google Scholar
11. Wegener, P. P. and Mack, L. M. Condensation in supersonic and hypersonic wind tunnels. Advances in Applied Mechanics, Vol. V, p. 307, 1958.CrossRefGoogle Scholar
12. Griffith, B. J., Deskins, H. E. and Little, H. R. Condensation studies in Hotshot tunnels. AIAA Journal, Vol. 2, No. 9, p. 1645, 1964.CrossRefGoogle Scholar
13. Fay, J. A. and Riddell, F. R. Theory of stagnation point heat transfer in dissociated air. Journal of the Aeronautical Sciences, Vol. 25, No. 2, p. 73, 1958.Google Scholar
14. Rhudy, J. P., Hiers, R. S. and Rippey, J. O. Investigation of hypersonic flow over blunted plates and cone. Arnold Engineering Development Center, AEDC TN-60-93, May 1960.CrossRefGoogle Scholar
15. Cleary, J. W. Effects of angle of attack and nose blunt ness on the hypersonic flow over cones. AIAA Paper 66-414, June 1966.CrossRefGoogle Scholar
16. Cleary, J. W. An experimental and theoretical investigation of the pressure distribution and flow fields of blunted cones at hypersonic Mach numbers. NASA TN D-2969, August 1965.Google Scholar