Hostname: page-component-77c89778f8-gq7q9 Total loading time: 0 Render date: 2024-07-22T18:18:31.506Z Has data issue: false hasContentIssue false
  • English
  • Français

Correlation of Constant Pressure Turbulent Boundary Layer Measurements on Insulated Walls

Published online by Cambridge University Press:  07 June 2016

J. A. P. Stoddart
J. A. P. Stoddart*
Affiliation:
British Aircraft Corporation, Preston Division
Get access

Summary

Measured characteristics of compressible constant pressure adiabatic turbulent boundary layers are correlated in an incompressible frame of reference with the aid of a modification of the well known Mager compressibility transformation. Quite good data collapse is obtained although the transformation is shown to be deficient in the outer regions of the boundary layer. The results will be used to produce data sheets of constant pressure adiabatic turbulent boundary layer properties.

Type
Research Article
Information
Aeronautical Quarterly , Volume 20 , Issue 2 , May 1969 , pp. 151 - 170
Copyright
Copyright © Royal Aeronautical Society. 1969

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. Mager, A. Transformation of the compressible turbulent boundary layer. Journal of the Aeronautical Sciences, pp 305–311, May 1958.Google Scholar
2. Culick, F. E. C. and Hill, J. A. F. A turbulent analog of the Stewartson-Illingworth transformation. Journal of the Aeronautical Sciences, pp 259–262, April 1958.Google Scholar
3. Coles, D. E. The turbulent boundary layer in a compressible fluid. Rand Corporation Report R-403-PR, September 1962.Google Scholar
4. Crocco, L. Transformation of the compressible turbulent boundary layer with heat exchange. AIAA Journal, pp 2723-2731, December 1963.Google Scholar
5. Van Driest, E. R. Turbulent boundary layer in compressible fluids. Journal of the Aeronautical Sciences, pp 145–160, March 1951.Google Scholar
6. Squire, H. B. and Young, A. D. The calculation of the profile drag of aerofoils. ARC R & M 1838, 1938.Google Scholar
7. Eckert, E. R. G. Engineering relations for friction and heat transfer to surfaces ia high velocity flow. Journal of the Aeronautical Sciences, pp 585–587, August 1955.Google Scholar
8. Coles, D. E. The law of the wake in the turbulent boundary layer. Journal of Fluid Mechanics, pp 191–226, 1956.Google Scholar
9. Baronti, P. O. and Libby, P. A. Velocity profiles in turbulent compressible boundary layers. AIAA Journal, pp 193–202, February 1966.Google Scholar
10. Korkegi, R. H. Transition studies and skin friction measurements on an insulated flat plate at a Mach number of 5-8. Journal of the Aeronautical Sciences, pp 97–107, February 1956.Google Scholar
11. Winter, K. G., Smith, K. G. and Gaudet, L. Measurements of turbulent skin friction at high Reynolds numbers at Mach numbers of 0-2 and 2-2. AGARDograph 97, pp 97–123, May 1965.Google Scholar
12. Moore, D. R. and Harkness, J. Experimental investigations of the compressible turbulent boundary layer at very high Reynolds numbers. AIAA Journal, pp 631–638, April 1965.Google Scholar
13. Hakkinen, R. J. Measurements of turbulent skin friction on a flat plate at transonic speeds. NACA TN 3486, September 1955.Google Scholar
14. Jackson, M. W., Czarnecki, K. R. and Monta, W. J. Turbulent skin friction at high Reynolds numbers and low supersonic velocities. NASA TN D-2687, March 1965.Google Scholar
15. Coles, D. E. Measurements of turbulent friction on a smooth flat plate in supersonic flow. Journal of the Aeronautical Sciences, pp 433–448, July 1954.CrossRefGoogle Scholar
16. McRee, D. I., Peterson, J. B. Jr. and Braslow, A. L. Effect of air injection through a porous surface and through slots on turbulent skin friction at Mach 3. NASA TN D-2427, August 1964.Google Scholar
17. Stalmach, C. J. Jr. Experimental investigations of the surface impact probe method of measuring local skin friction at supersonic speeds. University of Texas Defence Research Laboratories, DRL-410 CF-2675, January 1958.Google Scholar
18. Schutts, W. H., Hartwig, W. H. and Weiler, J. R. Turbulent boundary layer and skin friction measurements on a smooth, thermally insulated flat plate at supersonic speeds. University of Texas Defence Research Laboratory, DRL-364 CM-823, January 1955.Google Scholar
19. 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 TRR-82, 1961.Google Scholar
20. Klebanoff, P. S. Characteristics of turbulence in a boundary layer with zero pressure gradient. NACA Report 1247, 1955.Google Scholar
21. Smith, D. W. and Walker, J. H. Skin friction measurements in incompressible flow. NASA TRR-26, 1959.Google Scholar
22. O’Donnell, R. M. Experimental investigation at a Mach number of 2-41 of average skin friction coefficients and velocity profiles for laminar and turbulent boundary layers and an assessment of probe effects. NACA TN 3122, January 1954.Google Scholar
23. Wilson, R. E. Turbulent boundary layer characteristics at supersonic speeds—Theory and experiment. Journal of the Aeronautical Sciences, pp 585–594, September 1950.Google Scholar
24. Monaghan, R. J. and Johnson, J. E. The measurement of heat transfer and skin friction at supersonic speeds. Part II. Boundary layer measurements on a flat plate at Af=2-5 and zero heat transfer. RAE Technical Note, Aero 2031, December 1949.Google Scholar
25. Chapman, D. R. and Kester, R. H. Turbulent boundary layer and skin friction measurements in axial flow along cylinders at Mach numbers between 0-5 and 3-6. NACA TN 3097, December 1953.Google Scholar
26. Adcock, J. B., Peterson, J. B. Jr. and McRee, D. I. Experimental investigation of a turbulent boundary layer at Mach 6, high Reynolds numbers and zero heat transfer. NASA TN D-2907, July 1965.Google Scholar
27. Monaghan, R. J. and Cooke, J. R. The measurement of heat transfer and skin friction at supersonic speeds. Part IV. Tests on a flat plate at M = 2*82. RAE Technical Note Aero 2171, June 1952.Google Scholar
28. McLafferty, G. H. and Barber, R. E. Turbulent boundary layer characteristics in supersonic streams having adverse pressure gradients. United Aircraft Corporation, R-1285-11, September 1959.Google Scholar
29. Sterrett, J. R. and Emery, J. C. Extension of boundary layer separation criteria to a Mach number of 6-5 by utilising flat plates with forward-facing steps. NASA TN D-618, December 1960.Google Scholar
30. Nothwang, G. J. An evaluation of four experimental methods for measuring mean properties of a supersonic turbulent boundary layer. NACA Report 1320, 1957.Google Scholar
31. Roshko, A. and Thomke, G. J. Observations of turbulent reattachment behind an axisymmetric downstream facing step in supersonic flow. AIAA Journal, pp 975–980, June 1966.Google Scholar
32. Monaghan, R. J. and Cooke, J. R. The measurement of heat transfer and skin friction at supersonic speeds. Part III. Measurements of overall heat transfer and of the associated boundary layers on a flat plate at M=2·43. RAE Technical Note Aero 2129, December 1951.Google Scholar
33. Stoddart, J. A. P. Properties of constant pressure adiabatic turbulent boundary layers. BAC Aerodynamics Note Ae/A/290, February 1968.Google Scholar
34. Head, M. R. Entrainment in the turbulent boundary layer. ARC R & M, 3152. September 1958.Google Scholar