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The accuracy of flat plate, turbulent skin friction at supersonic speeds

  • L. C. Squire (a1)

Abstract

This paper presents a comparison of turbulent skin-friction coefficients measured by floating element balances in zero pressure gradient conditions for a wide range of Mach numbers and Reynolds numbers. From these comparisons it is clear that although a large number of measurements have been made it is impossible to use these measurements to find the skin-friction coefficient for a given Mach number and Reynolds number to an accuracy of better than ±2 to 3%. This estimate of accuracy applies only to the range of Mach numbers and Reynolds within which there are a reasonable number of measurements to compare. Outside this range, say for Reynolds numbers based on momentum thickness greater than 40,000 and Mach numbers greater than 2 the uncertainty is greater.

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(Direct references to most of the experimental data are not included here. These details are included in Refs 9 and 10 with the relevant data set numbers given in Table I.)

1. Huang, P.G., Bradshaw, P. and Coakley, T.J. Skin friction and velo city profile family for compressible boundary Layers, AIAA J. 1993, 33, pp 16001604.
2. Motallebi, F. Reynolds number effects on the prediction of mean flow data for adiabatic 2D compressible boundary layers, Aeronaut J, 1996, 100, pp 5359.
3. Van Driest, E.R. Turbulent boundary layers in compressible fluids, J Aeronautical Sci, 1951, 18, pp 145160.
4. Spaldfng, D.B. and Chi, S.W. The drag of a compressible boundary layer on smooth flat plate with and without heat transfer, J Fluid Mech, 1964, 8, pp 117143.
5. Winter, K.G. and Gaudet , L. Turbulent boundary-layer studies at high Reynolds numbers at Mach numbers between 0.2 and 2.8 ARC R & M 3712, 1970.
6. Fernholz, H.H. and Finley, P.J. A critical compilation of compressible boundary layer data. AGARD Report Ag-223, 1977.
7. White, F.M. and Christoph, G.H. J Basic Engineering, 1972, 94, pp 636642.
8. Mabey, D.G. Experimental Studies of the boundary layer on a flat plate at Mach numbers from 2.5 to 4.5, ARC R&M 3784, 1976.
9. Mabey, D.G. Some observations on the wake component of the veloc ity profiles of turbulent boundary layers at subsonic and supersonic speeds. Royal Aircraft Establishment Tech Report 77004, 1977.
10. Fernholz, H.H. and Finley, P.J., A further compilation of compressible boundary layer data with a survey of turbulence data AGARD Report Ag-263, 1981.
11. Gaudet, L. Experimental investigation of the turbulent boundary layer at High Reynolds numbers and a Mach number of 0.8. Royal Aircraft Establishment Tech Report 84094. 1984.
12. Fernholz, H.H. and Finley, P.J. A critical commentary on mean flow data for two-dimensional compressible turbulent boundary layers. AGARD Report Ag-253, 1980.

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The accuracy of flat plate, turbulent skin friction at supersonic speeds

  • L. C. Squire (a1)

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