Author : Bernard N. Daley
Publisher : Unknown
Page : 68 pages
File Size : 42,9 Mb
Release : 1949
Category : Aerofoils
ISBN : UOM:39015086464487
Aerodynamic Characteristics of Several 6-percent-thick Airfoils at Angles of Attack from 0 to 20 Degrees at High Subsonic Speeds by Bernard N. Daley Pdf
Two-dimensional tests of eight 6-percent-thick symmetrical airfoils of the supersonic and subsonic types were conducted in the Langley rectangular high-speed tunnel. The aerodynamic characteristics of each of the airfoils have been determined from the measured pressure data. These results showed that the lift-curve slope of each of the airfoils decreased rapidly to a positive value approaching zero at angles of attack near 9 degrees and roughly maintained this value up to the highest angle of attack tested.