Characteristics of Naca 4400R Series Rectangular and Tapered Airfoils, Including the Effect of Split Flaps
Description:
"At the request of the Bureau of Aeronautics, Navy Department, tests were made in the variable-density wind tunnel of a tapered wing of 3-10-18 plan form and based on the NACA 4400R series sections. The wing was also tested with 0.2 chord split flaps, deflected 60 degrees, in the center of the wing and having flat span to wing span ratios of 0.3, 0.5, 0.7, and 1.0, respectively" (p. 1).
Date:
January 1941
Creator:
Greenberg, Harry
Item Type:
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Partner:
UNT Libraries Government Documents Department