Year: 1943
Type: article
Abstract: Oharts are presented to show the effects of taper ratio, thickness ratio, aspeot ratio, and Reynolds number on the spanwlse location of the Initial wing stall and on ""the maxlmun lift coeffloiant of the wing.These stall " charts supplement the charts given in HACA Report Ho. 703 by including additional taper ratios and a root thickness " ratio of 0.24 tapering to 0.09 at the tip.Yor a root thickness ratio of 0.24, the effect of increasing the aspect ratio to 18 is Investigated..-..
Author: Sidney M Harmon
Language: English
Subfield: Computational Mechanics
Field: Engineering
Domain: Physical Sciences
Open Access status: green
OpenAlex ID: W333773036