Abstract
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.
Publisher
Cambridge University Press (CUP)
Reference1 articles.
1. Mangler W. The Lift Distribution of Wings with End Plates. T.M. No. 856, N.A.C.A., 1938.
Cited by
13 articles.
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