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Results of a Cyclic Load Test of an RB-47E AirplaneResults of a cyclic load test made by NASA on an EB-47E airplane are given. The test reported on is for one of three B-47 airplanes in a test program set up by the U. S. Air Force to evaluate the effect of wing structural reinforcements on fatigue life. As a result of crack development in the upper fuselage longerons of the other two airplanes in the program, a longeron and fuselage skin modification was incorporated early in the test. Fuselage strain-gage measurements made before and after the longeron modification and wing strain-gage measurements made only after wing reinforcement are summarized. The history of crack development and repair is given in detail. Testing was terminated one sequence short of the planned end of the program with the occurrence of a major crack in the lower right wing skin.
Document ID
19980232006
Acquisition Source
Headquarters
Document Type
Other - NASA Memorandum (MEMO)
Authors
Huston, Wilber B. (NASA Langley Research Center Hampton, VA United States)
Date Acquired
September 6, 2013
Publication Date
January 1, 1959
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
NASA-MEMO-3-15-59L
AF-AM-171
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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