Flight Investigation and Theoretical Calculations of the Fuselage Deformations of a Swept-Wing Bomber During Push-Pull Maneuvers
Description:
Report presenting the results of fuselage-deflection measurements at three stations on the fuselage of a swept-wing bomber (Boeing B-47A) during 12 push-pull maneuvers. The results are provided in the form of coefficients expressing the fuselage deflection due to normal-acceleration loads, pitching angular-acceleration loads, pitching angular-velocity loads, and the combined effect of zero-lift loads, fuselage dead weight, and landing-gear reactions. Comparisons of the theoretical and experimen…
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Date:
March 29, 1957
Creator:
Mayo, Alton P.
Item Type:
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Report
Partner:
UNT Libraries Government Documents Department