23rd Congress of International Council of the Aeronautical Sciences, 8-13 September, 2002, Toronto, Canada
Paper ICAS 2002-2.3.2

NUMERICAL OPTIMIZATION OF THE WING OF A SUPERSONIC AIRPLANE

S. Takovitsky
TsAGI, Russian Federation

Keywords: optimization, wing, supersonic airplane

A direct optimization method is developed to design the wing of a supersonic civil airplane. Aerodynamic characteristics of the airplane are calculated within the framework of a model based on Euler’s equations with taking into account surface friction drag. The optimization algorithm is based on a modification of Newton’s method. Drag is used as the objective function minimized under lift, longitudinal trim and volume constraints. A fast convergence to the optimum in case of the large number (more than 500) of the variables is provided.

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