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Volume 85 - February 1981

Contents

Page 5 of 7

Reviews

Library

Other

Research Article

  • Stress concentration in rectangular cut-outs under pure shear

  • B. Bandyopadhyay, R. Karmakar
  • Published online by Cambridge University Press:
    04 July 2016, pp. 111-112

  • The presence of cut-outs in shell structures causes perturbations in the original stress system, so that in the region of the cut-out the local stress level in the sheet may be increased many times. These stress concentrations can be considerably reduced, and in some cases entirely eliminated by the use of a suitably chosen shape of cut-out, and by the use of a suitable reinforcing member around the edge.

    The factors which influence the magnitude of these stress concentrations are the shape of the cut-out and the dimensions of the reinforcement. The geometry of the shell itself is generally of only secondary importance, provided that the size of the cut-out is small compared with the radius of curvature of the shell.

Other

Front matter

  • AER volume 85 issue 843 Cover and Front matter

  • Published online by Cambridge University Press:
    04 July 2016, pp. f1-f4
    • Article
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Reviews

Library

Front matter

  • AER volume 85 issue 841 Cover and Front matter

  • Published online by Cambridge University Press:
    04 July 2016, pp. f1-f4
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Research Article

  • Application of vortex lattice methods to calculate Lv (rolling moment due to sideslip)

  • M. A. Javed, G. J. Hancock
  • Published online by Cambridge University Press:
    04 July 2016, pp. 113-117

  • Lateral (asymmetric) aerodynamics of aircraft have received comparatively little attention compared with longitudinal (symmetric) aerodynamics of aircraft. Up to the present time, understanding, supported by effective and extensive numerical methods, has been built up on the attached flow past wings, wing-body combinations, etc, in symmetric conditions. It is now a natural progression to assess how far some of the predictive techniques for symmetric conditions can be extended to asymmetric conditions. Some of the surface panel methods have been developed purely for the symmetric case and their extension to an asymmetric flow is not merely a routine matter. As a preliminary step, to build up some experience and understanding of asymmetric flows, it is investigated how the standard vortex lattice model for finite wings might be modified to calculate the rolling moment on a finite wing due to steady sideslip (i.e. Lv, Clβ) at low speeds.

Other

Front matter

  • AER volume 85 issue 845 Cover and Front matter

  • Published online by Cambridge University Press:
    04 July 2016, pp. f1-f4
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  • AER volume 85 issue 846 Cover and Front matter

  • Published online by Cambridge University Press:
    04 July 2016, pp. f1-f4
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  • AER volume 85 issue 849 Cover and Front matter

  • Published online by Cambridge University Press:
    04 July 2016, pp. f1-f4
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Other

Back matter

  • AER volume 85 issue 848 Cover and Back matter

  • Published online by Cambridge University Press:
    04 July 2016, pp. b1-b2
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Front matter

  • AER volume 85 issue 840 Cover and Front matter

  • Published online by Cambridge University Press:
    04 July 2016, pp. f1-f4
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Page 5 of 7