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Optimization and design of an aircraft's morphing wing-tip demonstrator for drag reduction at low speeds, Part II- Experimental validation using Infra-Red transition measurement from Wind Tunnel tests 被引量:12

Optimization and design of an aircraft's morphing wing-tip demonstrator for drag reduction at low speeds, Part II- Experimental validation using Infra-Red transition measurement from Wind Tunnel tests
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摘要 In the present paper, an ‘in-house' genetic algorithm was numerically and experimentally validated. The genetic algorithm was applied to an optimization problem for improving the aerodynamic performances of an aircraft wing tip through upper surface morphing. The optimization was performed for 16 flight cases expressed in terms of various combinations of speeds, angles of attack and aileron deflections. The displacements resulted from the optimization were used during the wind tunnel tests of the wing tip demonstrator for the actuators control to change the upper surface shape of the wing. The results of the optimization of the flow behavior for the airfoil morphing upper-surface problem were validated with wind tunnel experimental transition results obtained with infra-red Thermography on the wing-tip demonstrator. The validation proved that the 2D numerical optimization using the ‘in-house' genetic algorithm was an appropriate tool in improving various aspects of a wing's aerodynamic performances. In the present paper, an ‘in-house' genetic algorithm was numerically and experimentally validated. The genetic algorithm was applied to an optimization problem for improving the aerodynamic performances of an aircraft wing tip through upper surface morphing. The optimization was performed for 16 flight cases expressed in terms of various combinations of speeds, angles of attack and aileron deflections. The displacements resulted from the optimization were used during the wind tunnel tests of the wing tip demonstrator for the actuators control to change the upper surface shape of the wing. The results of the optimization of the flow behavior for the airfoil morphing upper-surface problem were validated with wind tunnel experimental transition results obtained with infra-red Thermography on the wing-tip demonstrator. The validation proved that the 2D numerical optimization using the ‘in-house' genetic algorithm was an appropriate tool in improving various aspects of a wing's aerodynamic performances.
出处 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2017年第1期164-174,共11页 中国航空学报(英文版)
基金 Bombardier Aerospace,Thales Canada,The Consortium in Research and Aerospace in Canada(CRIAQ) the Natural Sciences and Engineering Research Council of Canada(NSERC)for their financial support
关键词 Drag reduction Infra-red tests Morphing wing OPTIMIZATION Wind tunnel tests Drag reduction Infra-red tests Morphing wing Optimization Wind tunnel tests
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