22nd Congress of International Council of the Aeronautical Sciences, Harrogate, UK, 28 August - 1st September, 2000
Paper ICAS 2000-2.1.3

SUPERSONIC INVERSE DESIGN OF WINGS FOR THE FULL CONFIGURATION OF JAPANESE SST

K. Matsushima (1), T. Iwamiya (2), H. Ishikawa (3)
(1) FUJITSU Ltd, Japan; (2) National Aerospace Lab, , Japan; (3) SANKO Systems Lab., Japan

Keywords: sst, full configuration, inverse wing design, aerodynamics

An inverse design method based on the residualcorrection concept has been developed and applied to aerodynamic design of wings for Japanese SST (supersonic transport). The method is a system of CFD (computational fluid dynamics) softwares. It designs the section geometry at every span station of a wing which realizes the prescribed target pressure distribution. It handles practical models of an aircraft up to a full configuration model. The design system consists of a supersonic inverse problem solver and a Navier-Stokes simulation code. The inverse problem solver has been newly formulated. By means of the design method, two challenging designs are taking place. The first one is the design of a high L/D wing for a wing-fuselage configuration. This has attained a satisfactory design result. The other is the design of a wing for a full configuration SST. For the second challenge, the feasibility has been confirmed that themethod can be applied to the design of the wing which

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