Estimation of the maximum angle of sideslip for determination of vertical-tail loads in rolling maneuvers

Ralph W. Stone, Jr.
naca-tn-2633
Feb 1952


Recent experiences have indicated that angles of sideslip in rolling maneuvers may be critical in the design of vertical tails for current research airplanes having weight distributed mainly along the fuselage. Previous investigations have indicated the seriousness of the problem for the World War II type of airplane. Some preliminary calculations for airplanes of current design, particularly with weight distributed primarily along the fuselage, are made herein.

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