A derivation of a theoretical model for the vertical autorotation of a samara wing is presented. The dynamic effects are treated in an accurate manner. The aerodynamic effects are calculated by using the blade element/momentum theory. Because of basic differences between the mode of operation of a samara wing and other rotary wings, the model differs from existing rotary wing models. An experimental setup, aimed at verifying the theoretical model, is also described. Comparison between theoretical and experimental results are presented.

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