22nd Congress of International Council of the Aeronautical Sciences, Harrogate, UK, 28 August - 1st September, 2000
Paper ICAS 2000-7.4.2

AERODYNAMIC CONFIGURATION DESIGN OF AIRCRAFT USING MULTI-OBJECTIVE GENETIC ALGORITHM

X. Wang, Z. Gao
Northwestern Polytechnical University, Xi'an, PRC

Keywords: numerical procedure, aerodynamic configuration, optimization, aircraft configuration

A numerical procedure for the aerodynamic configuration design of aircraft based on genetic algorithms, with single-point, multipoint and multi-objective optimization capabilities, is presented. Optimization process is executed based on a light fighter, which is composed of wing, body and horizontal tail. The geometry and relative position of three parts, wing, body and horizontal tail, are chosen as the design variables. The objective is to acquire the maximum lift-to-drag ratio under the given constraints. Three single-point designs in the subsonic, transonic and supersonic region have been first addressed. Then multi-point designs are taken under transonic and supersonic cases with three different weighted factors. Lastly, the pareto front of optimization design is obtained using multi-objective pareto genetic algorithms, and the designed results are shown under the same design condition as multi-point. A comparison between the results obtained in three ways is established, showing the effectiveness of multiobjective optimization used to deal with aerodynamic configuration design.

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