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�������պ����ѧѧ�� 1998, Vol. 24 Issue (3) :311-314    DOI:
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Effects of Vortex Generators on Maximum Lift and StallAngle of Attack over Wings
Shen Xialing1, Gao Ge2, Liu Baojie2, Yang Xiaoning2*
1. Beijing University of Aeronautics and Astronautics,Dept. of Flight Vehicle Design and Applied Mechanics;
2. Beijing University of Aeronautics and Astronautics,Dept. of Jet Propulsion

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ժҪ ��һ��չ��Ϊ500?mm,�ҳ�Ϊ250?mm,����ΪNACA0012�Ļ���ģ��,��װ����С���������з����������ٷ綴����ʵ��,�о�С�����������Ⱥ������������λ�öԻ������������ʧ��ӭ�ǵ�Ӱ��.ʵ����������С�������������ij��������λ��ʱ,�������������ʧ��ӭ���и���������.��С���������������λ�ò���ʱ,������ȵ�С����������ʹ�������������ʧ��ӭ���нϴ������,�����໥��𲻴�.
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Abstract�� The effects of locations and various cambers of small delta vortex generators on the maximum lift and stall angle of attack of wings are studied in the wind tunnel.The small delta vortex generators varied in cambers and locations are fixed on the wing model which has NACA 0012 of span 500?mm chord 250?mm.The test results show that when the delta generator is the optimum position on the wing,the maximum increase of the maximum lift coefficient and stall angle of attack of the wing may be obtained and that when the position of the delta generator is fixed,delta vortex generators of various cambers may be used to increase the maximum lift coefficient and stall angle of attack of the wing and their increments are not much difference.
Keywords�� wings   aerodynamic characteristics   vortex flow   vortex generators     
Received 1997-08-28;
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������, �߸�, ������, ������.���з������Ի������������ʧ��ӭ�ǵ�Ӱ��[J]  �������պ����ѧѧ��, 1998,V24(3): 311-314
Shen Xialing, Gao Ge, Liu Baojie, Yang Xiaoning.Effects of Vortex Generators on Maximum Lift and StallAngle of Attack over Wings[J]  JOURNAL OF BEIJING UNIVERSITY OF AERONAUTICS AND A, 1998,V24(3): 311-314
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