Hostname: page-component-586b7cd67f-gb8f7 Total loading time: 0 Render date: 2024-11-28T17:14:55.409Z Has data issue: false hasContentIssue false
  • English
  • Français

Fuselage Lift Distribution for a Swept-Back Wing Aircraft

Published online by Cambridge University Press:  28 July 2016

W. Taylor
W. Taylor*
Affiliation:
Vickers-Armstrongs, Supermarine
Get access Rights & Permissions [Opens in a new window]

Extract

This note suggests a method, suitable for stressing purposes, of obtaining a fuselage air-load distribution, for a swept-back wing aircraft. The method is basically that given in Ref. 1. Mach number effect on the aerodynamic centre position is discussed and an approximate method of allowing for this is suggested. A numerical example is given.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 57 , Issue 511 , July 1953 , pp. 464 - 467
Copyright
Copyright © Royal Aeronautical Society 1953

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. Schlichting, H. (1952). Calculation of the Influence of a Body on the Position of the Aerodynamic Centre of Aircraft with Swept-back Wings. R. & M. 2582, 1952. Google Scholar
2. Stanton Jones, R. (1950). An Empirical Method for Rapidly Determining the Loading Distributions on Sweptback Wings. College of Aeronautics Report No. 32, January 1950.Google Scholar