An analysis was made to determine the effect of rolling pull-out maneuvers on the wing and aileron loads of a typical fighter airplane, the P-47B. The results obtained indicate that higher loads are imposed upon wings and ailerons because of the rolling pull-out maneuver, than would be obtained by application of the loading requirements to which the airplane was designed. An increase of 102 lb or 15 percent of wing weight would be required if the wing were designed for rolling pull-out maneuver. It was also determined that the requirements by which the aileron was originally designed were inadequate.


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    Analysis of effect of rolling pull-outs on wing and aileron loads of fighter airplane

    Pearson, H.A. / Aiken, Jr., W.S. | Engineering Index Backfile | 1946




    Measurement and analysis of wing and tail buffeting loads on fighter airplane

    Huston, W.B. / Skopinski, T.H. | Engineering Index Backfile | 1955


    Airplane aileron execution mechanism

    SUN HUANYU / XU WENLIANG / SUN YONGHUAN et al. | Europäisches Patentamt | 2015

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