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)

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Report Number: AF TR 5761 Part 9
Author(s): Fung, Y. C.
Corporate Author(s): Guggenheim Aeronautical Laboratory
Laboratory: Air Materiel Command
Corporate Report Number: AD0108567
Date of Publication: 1950-10-01
Pages: 127
Contract: W33-038-ac-16961
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Provenance: Bombardier/Aero

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