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dc.creatorBrown, Charles G.en_US
dc.creatorGreene, Carl F.en_US
dc.date.accessioned2017-09-20T20:23:15Z
dc.date.available2017-09-20T20:23:15Z
dc.date.created1932-02-15en_US
dc.identifier.urihttp://hdl.handle.net/11200/48991
dc.descriptionThe object of the tests on the Materiel Division 55 foot cantilever all-metal wing was: 1. To determine its ultimate strength in high incidence for comparison with the strength indicated by the stress analysis. 2. The determination of the torsional characteristics of the complete wing. 3. The determination of contribution of the leading and trailing edges to the beam and the torsional rigidity of the wing. 4. The determination of the distribution of stress in the flanges of the wing due to chord, beam, and torque loads.en_US
dc.formatPDFen_US
dc.publisherWashington, D.C. : Chief of Air Corpsen_US
dc.relation.ispartofseriesAir Corps information circular (Aviation) ; v. 7, no. 663en_US
dc.relation.ispartofseriesAir Corps technical report ; Serial no. 3501en_US
dc.subjectAeronautics--Researchen_US
dc.subjectAeronautics--Systems engineeringen_US
dc.subjectAirplanes--Design and constructionen_US
dc.subjectAirplanes--Parts--Testingen_US
dc.subjectAirplanes--Wingsen_US
dc.subjectStrains and stressesen_US
dc.titleStatic-test and stress-distribution studies of the Materiel Division 55-foot cantilever all-metal wing (airplane branch report)en_US
dc.typeTexten_US


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