Hostname: page-component-cd9895bd7-gbm5v Total loading time: 0 Render date: 2024-12-25T06:45:00.807Z Has data issue: false hasContentIssue false
  • English
  • Français

The Evaluation of Local Skin Friction in Compressible Flow

Published online by Cambridge University Press:  04 July 2016

S. Sivasegaram
S. Sivasegaram*
Affiliation:
Formerly at Imperial College, London, now at the University of Ceylon.
Get access Rights & Permissions [Opens in a new window]

Extract

In a recent note, Allen has investigated the use of Preston tubes and Clauser charts for determining the skin friction in supersonic, boundary-layer flows. He concluded that the Preston tube was best used in conjunction with the law of the wall of Fenter and Stalmach but that the Baronti and Libby wall law was most suitable for determining local skin friction from velocity profiles; both methods are complex and do not permit the direct use of Clauser charts. The present note presents a simple transformation which permits incompressible Clauser charts to be used for the evaluation of skin friction in supersonic flows; the method is applicable to both adiabatic and nonadiabatic situations. Some conclusions, based on experimental experience, are drawn regarding the determination of skin friction by sub-layer methods.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 75 , Issue 731 , November 1971 , pp. 793 - 795
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. Allen, I. M. Use of Baronti-Libby transformation and Preston tube calibration to determine skin friction from velocity profiles. NASA TN D-4853, 1968.Google Scholar
2. Fenter, F. W. and Stalmach, C. J. Jr. The measurement of local turbulent skin friction at supersonic speeds by means of surface impact probes. DRL 392, CM 878 (contract NOrd-16498) Univ of Texas, 1957.Google Scholar
3. Baronti, P. O. and Libby, P. A. Velocity profiles in turbulent compressible boundary layers. AIAA Journal, Vol 1, No 2, pp. 193–202, 1966.Google Scholar
4. Crocco, L. Transformation of the compressible turbulent boundary layer in the heat exchange. AIAA Journal, Vol 1, pp. 2723–2731, 1963.Google Scholar
5. Sivasegaram, S. and Whitelaw, J. H. The prediction of turbulent, supersonic, two-dimensional, boundary-layer flows. Dept of Mechanical Engg, Imperial College, London, report BL/TN/A/23, 1969.Google Scholar
6. Adcock, J. B., Peterson, J. B. and Mcree, I. Experimental investigation of a turbulent boundary layer at Mach 6, high Reynolds number and zero heat transfer. NASA, TN D-2907, 1965.Google Scholar
7. Samuels, R. P., Peterson, J. B. and Adcock, J. B. Experimental investigation of the turbulent boundary layer at a Mach number of 6 with heat transfer at high Reynolds numbers. NASA TN D-3858, 1967.Google Scholar
8. Lobb, R. K., Winkler, E. M. and Persh, J. Experimental investigation of turbulent boundary layers in hypersonic flow. NAVORD Rep. 3880, 1955.Google Scholar
9. Sivasegaram, S. An experimental investigation of supersonic boundary-layer flows with pressure gradients. Dept of Mechanical Engg, Imperial College, London, report BL/TN/B/16, 1969.Google Scholar
10. Coles, D. Measurements in the boundary layer on a smooth flat plate in supersonic flow. Ill: The problem of the turbulent boundary layer. Report no 20-71, Pasadena, JPL, 1953.Google Scholar
11. Edwards, B. and Sivasegaram, S. An experimental investigation of Mach 2-2, turbulent boundary layers in nominally zero pressure gradients. Dept of Mechanical Engg, Imperial College, London, report BL/TN/3, 1968.Google Scholar
12. Matting, F. W., Chapman, D. R., Nyholm, J. R., and Thomas, A. G. Turbulent skin friction at high Mach numbers and Reynolds numbers in air and helium. NASA TR R-82, 1961.Google Scholar
13. Winter, K. G., Smith, K. G. and Gaudet, L. Measurements of turbulent skin friction at high Reynolds numbers and at Mach numbers of 0·2 and 2·2. AGARDograph 97, 1965.Google Scholar
14. Spalding, D. B. and Chi, S. W. The drag of a compressible turbulent boundary layer on a smooth flat plate with and without heat transfer. JFM, Vol 18, part 1, pp. 117–143, 1964.Google Scholar
15. Bradshaw, P. Unpublished work at NPL, 1967.Google Scholar