[an error occurred while processing this directive]
   
 
���¿��ټ��� �߼�����
   ��ҳ  �ڿ�����  ��ί��  Ͷ��ָ��  �ڿ�����  ��������  �� �� ��  ��ϵ����
�������պ����ѧѧ�� 2006, Vol. 32 Issue (03) :288-292    DOI:
���� ����Ŀ¼ | ����Ŀ¼ | ������� | �߼����� << | >>
����N-S���̵�β���淨����������������
����, ����ǿ, �����, ���ڳ�*
�������պ����ѧ ���տ�ѧ�빤��ѧԺ, ���� 100083
Wake integration method for airfoil drag evaluation using N-S equations
Liu Zhou, Zhu Ziqiang, Wang Xiaolu, Wu Zongcheng*
School of Aeronautic Science and Technology, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

ժҪ
�����
�������
Download: PDF (1370KB)   HTML 1KB   Export: BibTeX or EndNote (RIS)      Supporting Info
ժҪ �о��˼������������Ľ��ķ���——β���淨��β������ֵ�λ�ú���Ӧ�Ļ��ּ���.���ǿ�����ʱ�ֱ�����˱�����ֺ�β��������ø�������RAE2822������.�����ʾ,2�ַ���������ͬ�Ľ��,����β������ַ�������Ч��,��ʵ��ֵ�ǺϽϺ�.β���淨��,β����λ��Ӧ�������Ե����ҳ�����0.6~1.0֮��.β������ַ����л��ֽ�����������������ϸ��������,����Ԥ�ƶ����ʱ仯�����ά��������,�÷����и��������.
Service
�ѱ����Ƽ�������
�����ҵ����
�������ù�����
Email Alert
RSS
�����������
�ؼ����� β�������   �������   ��������   N-S����     
Abstract�� Minimal improved far field method for airfoil drag evaluation——wake integration method was introduced. The position of wake integration and associated integral technics were also discussed. Predicted drag values for a given airfoil(RAE2822 airfoil)were compared and discussed using the surface integration and wake integration methods under both subsonic and supercritical flow conditions. Numerical data show that the results of both methods are the same, which indicates the wake surface integration method is valid. The calculated values agree well with the experimental data. It also indicate that in the wake integration method, the location of wake integration surface should be set in the distance of 0.6~1.0 relative chord length from the trailing edge. In the mean time, the results of wake integration method is independent of the variation of detailed configuration surface. Wake integration method might be more potential for the complex three-dimensional configurations having large curvature variation on the surface compared with surface integration method.
Keywords�� wake integration   surface integration   drag evaluation   N-S equations     
Received 2005-04-07;
Fund:

������Ȼ��ѧ����������Ŀ(10472013); ���տ�ѧ����������Ŀ(04A51044)

About author: �� ��(1981-), ��, ������, ˶ʿ��,liuzhou buaa@hotmail.com.
���ñ���:   
����, ����ǿ, �����, ���ڳ�.����N-S���̵�β���淨����������������[J]  �������պ����ѧѧ��, 2006,V32(03): 288-292
Liu Zhou, Zhu Ziqiang, Wang Xiaolu, Wu Zongcheng.Wake integration method for airfoil drag evaluation using N-S equations[J]  JOURNAL OF BEIJING UNIVERSITY OF AERONAUTICS AND A, 2006,V32(03): 288-292
���ӱ���:  
http://bhxb.buaa.edu.cn//CN/     ��     http://bhxb.buaa.edu.cn//CN/Y2006/V32/I03/288
Copyright 2010 by �������պ����ѧѧ��