Hostname: page-component-cd9895bd7-mkpzs Total loading time: 0 Render date: 2024-12-25T06:39:17.132Z Has data issue: false hasContentIssue false
  • English
  • Français

Investigation of the Possibilities of Rotating Cylinders as an Auxiliary Lift Device

Published online by Cambridge University Press:  04 July 2016

J. E. Chacksfield
J. E. Chacksfield*
Affiliation:
Miles Electronics Limited
Get access Rights & Permissions [Opens in a new window]

Extract

The following is an attempt to show the gains and losses achieved when a rotating cylinder is used to create additional lift during the take-off and landing of an aircraft.

A hundred-year old theory lies behind the results (the “Magnus” effect), which, up to the present day has not been put to practical use in flight for increasing CL. Many proposals and tentative designs have been studied at major Research Establishments, notably A.V.A. Gottingen and the RAE but experimental studies on aircraft converted for the purpose have yet to be made.

Limited test results show that the CL on a rotating cylinder can be as great as 15 providing that sufficient care is taken to approach infinite aspect ratio by means of end-plates on a high aspect ratio cylinder. The one great disadvantage with the cylinder is the high drag coefficients produced. However, there seems no reason why a fairing should not be placed in the wake to reduce the drag to that corresponding to a blunt-nosed thick aerofoil section.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 68 , Issue 647 , November 1964 , pp. 777 - 780
Copyright
Copyright © Royal Aeronautical Society 1964

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.Neumark, S.Rotating Aerofoils and Flaps. Journal of the Royal Aeronautical Society,January 1963.Google Scholar