Hostname: page-component-84b7d79bbc-g78kv Total loading time: 0 Render date: 2024-07-25T13:14:30.747Z Has data issue: false hasContentIssue false
  • English
  • Français

A Simple Approximation Method for Obtaining the Spanwise Lift Distribution*

Published online by Cambridge University Press:  28 July 2016

O. Schrenk
Get access Rights & Permissions [Opens in a new window]

Extract

In this paper a simple approximation method is presented for rapidly computing the lift distributions of arbitrary aerofoils. The numerical results are compared with those obtained by an exact method and for many purposes show a satisfactory degree of accuracy. The latter, for all practically occurring cases, can be estimated at the start of the computation work with the aid of the comparison examples given.

Type
National Advisory Committee for Aeronautics
Information
The Aeronautical Journal , Volume 45 , Issue 370 , October 1941 , pp. 331 - 336
Copyright
Copyright © Royal Aeronautical Society 1941

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.)

Footnotes

*

“ Ein einfaches Näherungsverfahren zur Ermittlung von Auftriebsverteilungen längs der Tragflügelspannweite.” Luftwissen; Bd. 7, Nr. 4, April 1940, pp.118–120.

References

1. Mangler, W. The Lift Distribution of Wings with End Plates. T.M. No. 856, N.A.C.A., 1938.Google Scholar