Hostname: page-component-78c5997874-j824f Total loading time: 0 Render date: 2024-11-04T22:43:42.903Z Has data issue: false hasContentIssue false
  • English
  • Français

Heat Transfer to Slender Bodies at a Mach Number of 5.2

Published online by Cambridge University Press:  07 June 2016

R. K. Fancett
R. K. Fancett*
Affiliation:
Royal Armament Research and Development Establishment
Get access

Summary

Because of the lack of reliable data on heat transfer to long bodies, measurements have been made to cone-cylinder-flares at a Mach number of 5·2. Axial heat transfer distributions were closely predicted by a modified reference enthalpy method for both laminar and turbulent flows at zero incidence and the heat transfer to the flare windward generator at incidence agreed with laminar theory.

Type
Research Article
Information
Aeronautical Quarterly , Volume 22 , Issue 1 , February 1971 , pp. 12 - 24
Copyright
Copyright © Royal Aeronautical Society. 1971

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. Engineering relations for skin friction and heat transfer to surfaces in high velocity flows. Journal of the Aeronautical Sciences, Vol. 22, No. 8, 1955.Google Scholar
2. Reshotko, E. Laminar boundary layer with heat transfer on a cone at angle of attack in a supersonic stream. NACA TN 4152, Dec 1957.Google Scholar
3. Wittliff, C. E. and Wilson, M. R. Heat transfer to slender cones in hypersonic airflow including yaw and nose-bluntness effects. Paper No. 61-213-1907, National IAS/ARS Joint Meeting, June 1961.Google Scholar
4. Picken, J. and Woodley, J. G. Notes on a discussion on boundary layer transition at hypersonic speeds. ARC 29904, Hyp. 675, Nov 1967.Google Scholar
5. Bowman, J. E. and Clayden, W. A. Reduction of base drag by base ejection. To be published.Google Scholar
6. 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 number. NASA TR R-104, 1961.Google Scholar