著者

上田 哲彦 UEDA Tetsuhiko

出版者

航空宇宙技術研究所

雑誌

航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-785 (ISSN:03894010)

巻号頁・発行日

vol.785, pp.14, 1983-11

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A method to predict unsteady aerodynamic forces on lifting surfaces in supersonic flow is presented. The wing is divided into small segments in which the lift force is expressed by a single point doublet of the acceleration potential. This is the same concept as the doublet point method developed by the authors for subsonic flows. In order to avoid sensitiveness to the Mach number, the upwash due to the point doublet is calculated by averaging over small areas. The integration is done analytically so that it requires no numerical quadrature. Pressure distributions are directly obtained as the unknowns of an algebraic equation. The results are compared with those obtained by other methods for various wing geometries including the AGARD Wing-tail configuration.

著者

上田 哲彦 UEDA Tetsuhiko

出版者

航空宇宙技術研究所

雑誌

航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-781 (ISSN:03894010)

巻号頁・発行日

vol.781, pp.13, 1983-10

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A simple method for calculating the unsteady aerodynamic loadings on harmonically oscillating thin wings in subsonic flow has been developed. The method is basaed on a concept of concentrated lift forces. The wing is divided into the element surfaces on which lift distributions are represented by single concentrated lift forces. Since the procedure does not include any quadratures, it can easily be applied to calculate the unsteady aerodynamic loadings on complex planform wings even when they have partial span control surfaces. Numerical calculations are carried out for various wing geometries and are compared with other analyses and experiments.