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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