Hostname: page-component-cd9895bd7-q99xh Total loading time: 0 Render date: 2024-12-25T06:08:12.165Z Has data issue: false hasContentIssue false
  • English
  • Français

Interference Effects in an Infinite Cascade of Wings of Finite Span

Published online by Cambridge University Press:  04 July 2016

B. Lakshmi Narayana
B. Lakshmi Narayana*
Affiliation:
Department of Mechanical Engineering, The University of Liverpool
Get access Rights & Permissions [Opens in a new window]

Extract

Using Glauert's three-dimensional aerofoil theory, an expression for the induced velocity due to the trailing vortices of an infinite cascade of wings of finite span has been derived. The reduction in the average lift coefficient due to these induced velocities has been evaluated for some cases. It is shown that for a cascade of low space-chord ratio, the reduction in lift due to the interference from the trailing vortices is quite considerable.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 66 , Issue 619 , July 1962 , pp. 460 - 461
Copyright
Copyright © Royal Aeronautical Society 1962

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.Glauert, H. (1948). Aerofoil and Airscrew Theory. Cambridge University Press, Cambridge, 1948.Google Scholar
2.Horlock, J. H. (1958). Axial Flow Compressors. Butterworth, London, 1958.Google Scholar
3.Thwaites, B. (1960) Incompressible Aerodynamics, p. 531. Clarendon Press. Oxford, 1960.Google Scholar
4.Pistolesi, E. (1941). On the Calculation of Flow Past an Infinite Screen of Thin Aerofoils. NACA Tech. Memo. 968.Google Scholar