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Theoretical and Experimental Effect of Sweep upon the Stress and Deflection Distribution in Aircraft Wings of High Solidity: Part 16. Stress and Deflection Tests on Two Full Span 45 Degree Swept Plates of Different Thickness Distribution With Various Support Conditions
Author(s): Sechler, E. E., Beebe, W. M.
Corporate Author(s): Guggenheim Aeronautical Laboratory, California Institute of Technology
Laboratory: Aircraft Laboratory
Date of Publication: 1952-07
Report number: AF TR 5761 Part 16

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