A Simple approximation method for obtaining the spanwise lift distribution

Schrenk, O.
naca-tm-948
1940


In this paper a simple approximation method is presented for rapidly computing the lift distributions of arbitrary airfoils. 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.

An Adobe Acrobat (PDF) file of the entire report:
http://naca.central.cranfield.ac.uk/reports/1940/naca-tm-948.pdf