Skip to main content Accessibility help

We use cookies to distinguish you from other users and to provide you with a better experience on our websites. Close this message to accept cookies or find out how to manage your cookie settings.

Close cookie message
×
  1. Home
  2. Journals
  3. The Aeronautical Journal
  4. Volume 84
Journal Home
Refine listing

Refine listing

Access:
Publication date:

Actions for selected content:

Select all | Deselect all
  • View selected items
  • Export citations
  • Download PDF (zip)
  • Save to Kindle
  • Save to Dropbox
  • Save to Google Drive

Save Search

You can save your searches here and later view and run them again in "My saved searches".

Please provide a title, maximum of 40 characters.
Cancel
×

Volume 84 - February 1980

Contents

Page 4 of 7

Reviews

Library

Technical Note

  • Wing flapping with minimum energy

  • R. T. Jones
  • Published online by Cambridge University Press:
    04 July 2016, pp. 214-217

  • The interesting article by Archer, Sapuppo and Betteridge leads to the problem of determining the optimum lift distribution along the wing during flapping motion. Adopting the assumptions made in Ref. 1, the problem may be reduced to one of minimising the induced drag for a specified, periodically varying, bending moment at the wing root. The wing-root bending moment should be of primary importance to a bird or, for that matter, to a mechanical flapping-machine, since it is at this point that most of the flapping energy is introduced.

Other

Reviews

Library

Other

Reviews

Library

Technical Notes

  • The effect of trailing-edge strips on the unsteady aerodynamic forces on a control surface

  • G. Long, P. A. Farrell
  • Published online by Cambridge University Press:
    04 July 2016, pp. 388-391

  • A modification sometimes used to increase the effectiveness of a control surface is thickening of the trailing-edge by attaching small spanwise strips, normal to the upper and lower surface of the control, along the trailing-edge (see Fig. 1). While the effect of such a modification is fairly well known for steady flow, little evidence is available of the effect in unsteady flow. There are no theoretical methods of predicting the unsteady aerodynamic forces acting on an oscillating control surface which has trailing-edge strips (T-strips) attached and so flutter calculations are based on classical thin-liftingsurface theories. This practice is very dubious and two instances where flutter has occurred but has not been predicted by use of the classical unsteady aerodynamic forces, are described in Refs. 2 and 3.

Reviews

Library

SYMPOSIUM ON “Is Flight simulation of academic interest?”

Reviews

Library

Technical Notes

  • The drag of slant-based bodies of revolution

  • D. J. Maull
  • Published online by Cambridge University Press:
    04 July 2016, pp. 164-166

  • The drag of slant-based three-dimensional bodies such as the upswept rear fuselage of some aircraft (see for instance McCluney and Marshall and Peake) and car shapes (Morel) can be high and it is generally recognised that this high drag is associated with powerful longitudinal vortices in the flow direction. Morel has shown that the formation of these vortices, and therefore the drag, is a function of the slant angle of the base. His experiments were conducted with the body at zero incidence only and it appears that the effect of body incidence on the drag is unrecorded, although Bearman mentions that it has a significant effect.

Other

Library

Front matter

  • AER volume 84 issue 837 Cover and Front matter

  • Published online by Cambridge University Press:
    04 July 2016, pp. f1-f3
    • Article
      • You have access
    • PDF
    • Export citation

Reviews

Library

Page 4 of 7