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.