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Aeroelastic studies on a high-performance swept-wing airplane

Pengelley, C. Desmond and Benun, David (1951) Aeroelastic studies on a high-performance swept-wing airplane. California Institute of Technology , Pasadena, CA. (Unpublished)

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Comprehensive aeroelastic analyses and wind tunnel tests have been conducted on a model of a typical high-performance airplane with swept surfaces. The investigation covered the effect of dynamic pressure upon steady state longitudinal control and stability characteristics as well as aileron effectiveness. The analysis was based upon a superposition method which yields a convergent series which may be applied to any structure on which the load is a function of the deflection. It has been shown that after a few terms this series degenerates to an elementary geometric progression which maybe summed to infinity. This conclusion is applicable even to cases where the aeroelastic effects are large and the structure is actually approaching a condition of instability. Wind tunnel tests were carried out both at the Massachusetts Institute of Technology and the California Institute of Technology. Measured data were compared with the results of the theoretical analysis.

Item Type:Report or Paper (Technical Report)
Record Number:CaltechAUTHORS:20151130-135947096
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Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:62458
Deposited By: Kristin Buxton
Deposited On:03 Dec 2015 04:13
Last Modified:03 Oct 2019 09:19

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