22nd Congress of International Council of the Aeronautical Sciences, Harrogate, UK, 28 August - 1st September, 2000
Paper ICAS 2000-2.1.R1

OPTIMIZATION OF A GIVEN PLANFORM LIFTING SYSTEM AT SUPERSONIC SPEED

V. A. Silantiev, A.V. Ignatieva
SibNIA, Russia

Keywords: supersonic, linear theory, optimization task, variation method, lift coefficient, volume, induced-wave drag, lift-zero drag, middle surface, cross-section shape, fuselage axis.

The optimization problem of complex configurations is solved in the framework of the linear theory. Such variations of local incline angles of surface's elements are determined which lead to reduction of wave drag coefficient but keep the given magnitude of lift and pitching moment coefficients and also wing volume or areas of the wing cross-sections. For solving the problem of optimization the variation method is used. The Reverse Flow Theorem is lied in its base. The results showing the necessity to consider the optimization problem not only for wing separately, but also for complete configuration containing all lifting surfaces and fuselage are presented. The numerical analysis of thick wing-body configuration confirmed the correctness in the estimations of the inducedwave drag reduction, which was obtained by the linear theory. Also it confirmed the opportunity to determine an optimum fuselage axis deformation on the basis of the linear theory.

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