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Theoretical and Experimental Effect of Sweep upon the Stress and Deflection Distribution in Aircraft Wings of High Solidity: Part 9. On the Stresses in Cantilever Plates of Arbitrary Planform and Variable Thickness (A Relaxation Procedure With Applications to the Swept Wing Problem)Author(s): Fung, Y. C.
Corporate Author(s): Guggenheim Aeronautical Laboratory
Laboratory: Air Materiel Command
Date of Publication: 1950-10-01
Report number: AF TR 5761 Part 9