Hostname: page-component-cd9895bd7-gbm5v Total loading time: 0 Render date: 2024-12-22T15:39:03.418Z Has data issue: false hasContentIssue false
  • English
  • Français

The Design and Work of the Farnborough High Speed Tunnel

Published online by Cambridge University Press:  28 July 2016

A. Thom  and
W. G. A. Perring
Get access Rights & Permissions [Opens in a new window]

Extract

The importance of the effects of compressibility on the performance and behaviour of high speed aircraft has been appreciated for a great many years, but in this country it was not until 1937 that serious attention was given to the design of a wind tunnel that would enable the study of compressibility to be undertaken by tests on models of reasonable scale. Prior to 1937 the work which had gone on had established the characteristics of a few aerofoils and simple shapes; at Farnborough the work mainly related to the testing of high tip speed propellers, while at the National Physical Laboratory tests had been made of a two-dimensional character on aerofoils, these tests being made in a small wind tunnel driven on the injector principle, by air discharged from a high pressure reservoir.

Type
Research Article
Information
The Aeronautical Journal , Volume 52 , Issue 448 , April 1948 , pp. 205 - 250
Copyright
Copyright © Royal Aeronautical Society 1948

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

Note on page 225 * From elementary theory we have Ho–Po=½ρV2 (l+¼M 2+ …)

Hence V2 = 2 (Ho–Po)/ρ(l+¼M 2+ …)

If a is the velocity of sound in the undisturbed tunnel, a 2=γPo/ρ. Hence M 2 = V 2/a 2 = 2 (Ho–Po)/γPo (l+¼M 2 …)

so that M is simply a function of the pressure ratio (Ho–Po)/Po and so can be expressed (graphically) as a function of (p1–P2)/p2 .

Note on page 234 * High Speed Performance. W. G. A. Perring. Proceedings, Anglo-American Conference, R.Ae.S., London, 1948.

Note on page 245 * Modern Developments for Fluid Dynamics, p. 630.