翼形断面のねじりせん断応力
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概要
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The torsional shearing stress on the surface of an aerofoil section was studied. The analysis was carried out in the polar co-ordinate system. The back edge point of an aerofoil section was located on origin and the chord of the blade was located on the polar axis. The stress function was deduced by adapting conditions to satisfy the Poisson equation and the boundary of the section. By substituting the stress function into the fundamental formula, the torsional shearing stress at any point on the surface of the aerofoil section was found. Also the area and the polar moment of inertia of the aerofoil section were studied by the method of complex mapping function. Consequently, the torsional rigidity of the aerofoil section was deduced. As an example, the shearing stress distributions and the torsional rigidity of the Clark-Y series Propeller were calculated.
- 一般社団法人日本機械学会の論文
- 1987-12-25