縮む流體における二次元翼の理論

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§23. In this paper a method of "thin-wing-expansion" is developed for treating a uniform flow of a compressible fluid past an arbitrary aerofoil. In particular, analytical expressions are determined for the velocity potential and stream function to the order of ε^2, ε being some measure of the magnitude of disturbance due to the aerofoil. Further, explicit formulae, correct to the order of ε^2, are found for the lift and moment as well as for the velocity and pressure distributions for an arbitrary aerofoil. Finally, it is pointed out that the method of thin-wing-expansion can be successfully applied to the investigation of the asymptotic behaviour of compressible fluid flow at a great distance from an aerofoil submerged in it [3].
宇宙航空研究開発機構の論文