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�������պ����ѧѧ�� 2004, Vol. 30 Issue (05) :461-465    DOI:
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Comparison between adaptive and biobjective optimization wing's aerodynamic features
Liu Hang, Zhu Ziqiang, Fu Hongyan, Yu Rixin*
School of Aeronautic Science and Technology, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

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ժҪ �ڶ�ά��������Ӧ���о�������,��Powell���Ż������˶�ǰԵ���ӽ�Ϊ35°,չ�ұ�Ϊ3.9,�Ҹ���Ϊ0.17,��������ΪNACA65006���͵��������ǰ��Ե����ƫת��,�Ӷ���������ǿ�����ʱ����ȴ���ڳ�����ʱ����ϵ��С������Ӧ�����������������.�����˲����Ŵ��㷨,������Ҫ���ǿ���������ȴ�ͬʱ����������С������˫Ŀ���Ż����������.�������Ż����������ԭʼ�������������.���άһ��,��ά��ֵ����Ҳ֤��������Ӧ����ɻ�����Ե���������.
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Abstract�� Based on two dimensional airfoil adaptation, the deflected angles of leading edge and training edge of a three dimensions wing having 35° leading edge sweep angle, aspect ratio of 3.9, taper ratio of 0.17 and taking NACA65006 as wing section were calculated by using powell method to obtain an adaptive wing configuration having high lift/drag at subsonic/transsonic flight and low drag at supersonic flight. A biobjective optimizal wing was also designed for above 2 objectives, by using parallel Genetic Algorithm. The relative aerodynamical gains of both two optimal wings over the original wing were analyzed. Numerical results show that the adaptive wing can also obtain higher gains over the original and biobjective wings ,as illustrated in two dimensions.
Keywords�� Euler equation   adaptive wing   numerical optimization     
Received 2002-12-24;
Fund:

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����, ����ǿ, ������, ������.����Ӧ��˫Ŀ���Ż�������������ԱȽ�[J]  �������պ����ѧѧ��, 2004,V30(05): 461-465
Liu Hang, Zhu Ziqiang, Fu Hongyan, Yu Rixin.Comparison between adaptive and biobjective optimization wing's aerodynamic features[J]  JOURNAL OF BEIJING UNIVERSITY OF AERONAUTICS AND A, 2004,V30(05): 461-465
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