Proposed method of determining design tail loads for airplanes (airplane branch report)
Roche, J. A.
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DescriptionThe object of this report is to present a rational method for determining the values of design loads to be used for airplane horizontal tail surfaces and fuselage tail structures. This report gives (a) Sample computations for the determination of tail loads. (b) Tail-load curves and velocity diagrams for several service airplanes of the Air Corps. (c) A ruling which is recommended as a substitute in the Handbook of Instructions for the present arbitrary tail surface design loads and wing diving load factors. (d) An appendix presenting a precise method for the computation of tail loads, and justifying the use of the approximate method by which the tail-load curves given in this report were obtained.
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