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A Comparison of the Spanwise Loading Calculated by Various Methods With Experimental Loadings Obtained on a 45 Degree Sweptback Wing of Aspect Ratio 8.02 at a Reynolds Number of 4.0 X 10(6)
"This report compares the experimental force and moment data obtained by pressure measurements on a wing of aspect ratio 8.02, 45 degree sweptback of the quarter-chord line, taper ratio of 0.45, and NACA 63(sub 1)A012 airfoil sections with the calculated loadings obtained by the standard methods proposed by Weissinger, Falkner, and Multopp, as well as by several variations of these methods" (p. 1175).
Date:
August 14, 1951
Creator:
Schneider, William C.
System:
The UNT Digital Library
Flight tests on U.S.S. Los Angeles Part 1: full scale pressure distribution investigation
The primary purpose of this investigation was to obtain simultaneous data on the loads and stress experience in flight by the U. S. S. Los Angeles which could be used in rigid airship structure design. A secondary object of the investigation was to determine the turning and drag characteristics of the airship. The aerodynamic loading was obtained by measuring the pressure at 95 locations on the tail surfaces, 54 on the hull, and 5 on the passenger car. These measurements were made during a series of maneuvers consisting of turns and reversals in smooth air and during a cruise in rough air which was just short of squall proportions.
Date:
August 14, 1928
Creator:
De France, S. J.
System:
The UNT Digital Library