Hostname: page-component-78c5997874-lj6df Total loading time: 0 Render date: 2024-11-04T03:05:18.720Z Has data issue: false hasContentIssue false
  • English
  • Français

The independence of upper and lower wing flows at supersonic speeds

Published online by Cambridge University Press:  04 July 2016

L. C. Squire
L. C. Squire*
Affiliation:
Cambridge University Engineering Department
Get access Rights & Permissions [Opens in a new window]

Extract

Advances in computational methods are producing a need for accurate and detailed experimental results for test cases. At the same time economic trends force many of these experiments to be made in small wind tunnels. In some cases the small scale of the model does not provide enough space for the instrumentation and so the model must be distorted from the ideal shape. This paper is concerned with one aspect of this problem, that is, with the need to make wings thicker than required, either for strength or to provide volume for pressure tubes and other measuring devices. In particular the paper deals with the conditions under which the pressures measured on the flat surfaces of wings with bevelled or triangular cross-sections as shown in Figs. 1(b) and 1(c) are a good representation of the pressures which would be measured on the corresponding flat surface of thin wings (Fig. 1(a)). This problem has been touched on in a number of papers reporting experimental results but it does not appear to have been tackled systematically. The discussion of this paper is based on these earlier tests and on some new test results.

Type
Technical note
Information
The Aeronautical Journal , Volume 80 , Issue 790 , October 1976 , pp. 452 - 456
Copyright
Copyright © Royal Aeronautical Society 1976 

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. Rein, J. A. Flow over the suction surface of sharp edge delta wings with detached leading edge shock waves. Australian WRE Tech Note HSA 102, 1964.Google Scholar
2. Squire, L. C. Pressure distributions and flow patterns at M = 40 on some delta wings. ARC R & M 3373, 1964.Google Scholar
3. Squire, L. C. Flow regimes over delta wings at supersonic and hypersonic speeds. Aeronautical Quarterly, Vol XXVII, pp 1–14, 1976.Google Scholar
4. Yegna Narayan, K. The flow over a ‘high’ aspect ratio gothic wing at supersonic speeds. Aeronautical Quarterly, Vol XXVI, pp 189–201, 1975.Google Scholar