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A new boundary layer wind tunnel

Published online by Cambridge University Press:  04 July 2016

P. E. Roach
P. E. Roach*
Affiliation:
Advanced Research Laboratory, Rolls-Royce plc, Derby
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Summary

The procedures employed for the design of a closed-circuit, boundary layer wind tunnel are described. The tunnel was designed for the generation of relatively large-scale, two-dimensional boundary layers with Reynolds numbers, pressure gradients and free-stream turbulence levels typical of the turbomachinery environment. The results of a series of tests to evaluate the tunnel performance are also described. The flow in the test section is shown to be highly uniform and steady, with very low (natural) free-stream turbulence intensities. Measured boundary layer mean and fluctuating velocity profiles were found to be in good agreement with classical correlations. Test-section free-stream turbulence intensities are presented for grid-generated turbulence: agreement with expectation is again found to be good. Immediate applications to the tunnel include friction drag reduction and boundary layer transition studies, with future possibilities including flow separation and other complex flows typical of those found in gas turbines.

Type
Research Article
Information
The Aeronautical Journal , Volume 92 , Issue 916 , July 1988 , pp. 224 - 229
Copyright
Copyright © Royal Aeronautical Society 1988 

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