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Design methodology and performance of an indraft wind tunnel

Published online by Cambridge University Press:  03 February 2016

G. Johl ,
M. Passmore  and
P. Render
G. Johl
Affiliation:
Department of Aeronautical and Automotive Engineering, Loughborough University, Loughborough, UK
M. Passmore
Affiliation:
Department of Aeronautical and Automotive Engineering, Loughborough University, Loughborough, UK
P. Render
Affiliation:
Department of Aeronautical and Automotive Engineering, Loughborough University, Loughborough, UK
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Abstract

The design methodology and performance of Loughborough University’s new 1·9m × 1·3m, indraft wind tunnel is discussed in the following paper. To overcome severe spatial and financial constraints, a novel configuration was employed, with the inlet and exit placed adjacent to each other and opened to atmosphere. Using a fine filter mesh, honeycomb, two turbulence reduction screens and a contraction ratio of 7·3, flow uniformity in the working area of the jet at 40ms-1 is shown to be within 0·3% deviation from the mean velocity, with turbulence intensity in the region of 0·15%. Working section boundary layer characteristics are shown to be consistent with that of a turbulent boundary layer growing along a flat plate, which originates at the point of inflection of the contraction. A maximum velocity of 46ms-1 was achieved from a 140kW motor, compared to a prediction of 44ms-1, giving an energy ratio of 1·42. Comparison between theoretical and measured performance metrics indicate differences between the way modules perform when part of a wind tunnel system compared to data gathered from test rigs.

Type
Research Article
Information
The Aeronautical Journal , Volume 108 , Issue 1087 , September 2004 , pp. 465 - 473
Copyright
Copyright © Royal Aeronautical Society 2004 

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