THE present article is the application of Schrenk's approximate method to two cases, one a wing without twist and the other the same wing with twist, the nomenclature of Schrenk's article having been altered to conform to British usage, and a certain amount of explanatory matter added in order to make the method more easily understood.
Wing Lift Distribution
Aircraft Engineering and Aerospace Technology ; 16 , 5 ; 136-139
01.05.1944
4 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Engineering Index Backfile | 1944
|Spanwise Lift Distribution for Blended Wing Body Aircraft
Online Contents | 2005
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