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Theoretical and Experimental Effect of Sweep upon the Stress and Deflection Distribution in Aircraft Wings of High Solidity: Part 8. Some Experimental Data on the Deflection and Root Stresses in a Cantilever Triangular Plate of Constant Thickness With Varying Trailing Edge Sweep Angle
Author(s): Hrebec, G. M.
Corporate Author(s): Guggenheim Aeronautical Laboratory, California Institute of Technology
Laboratory: Air Materiel Command
Date of Publication: 1950-11-01
Report number: AF TR 5761 Part 8

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