Hostname: page-component-848d4c4894-mwx4w Total loading time: 0 Render date: 2024-07-01T20:59:51.374Z Has data issue: false hasContentIssue false

Some Effects of Thickness on the Longitudinal Characteristics of Sharp-Edged Delta Wings at Low Speeds

Published online by Cambridge University Press:  04 July 2016

L. C. Squire*
Affiliation:
Cambridge University Engineering Laboratory

Extract

Recently there has been renewed interest in the concept of an all-wing aircraft as a means of producing cheap air transport over relatively short distances. It is natural that with the large amount of information on slender wings now available an all-wing aircraft based on a sharp-edged slender planform should be considered for this role. One of the difficulties immediately faced in developing this concept is that since the aircraft must carry a large number of passengers it is necessary that as much of the wing area as possible should be deep enough to provide for a large passenger cabin. Thus the wing will be very thick over a large part of its area. If this condition is not met, then the aircraft has too much wing area and hence too high a structure weight. Typically one may think of an aircraft with a delta wing of aspect ratio 2 and with a wing thickness of from 15% to 20% of the root chord over as much of the wing area as possible. At first sight thickness of this order eliminates the main advantage of slender wings since the effect of thickness is usually to reduce the strength of the leading-edge vortices and hence the non-linear lift. Thus the incidence for a given lift is increased above that for a thin wing. This in turn means that the lift-to-drag ratio may be smaller.

Type
Technical notes
Copyright
Copyright © Royal Aeronautical Society 1968 

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. Gates, S. B. Wraps for air travellers. (Unpublished.)Google Scholar
2. Squire, L. C. Camber effects on the non-linear lift of slender wings with sharp leading edges. ARC Current Paper 924, 1966.Google Scholar
3. Peckham, D. and Atkinson, S. A. Preliminary results of low-speed tunnel tests on a gothic wing of aspect ratio 1.0. ARC 19457. 1957. Google Scholar