[an error occurred while processing this directive]
���¿��ټ��� �߼�����
   ��ҳ  �ڿ�����  ��ί��  Ͷ��ָ��  �ڿ�����  ��������  �� �� ��  ��ϵ����
�������պ����ѧѧ�� 2006, Vol. 32 Issue (06) :645-648    DOI:
���� ����Ŀ¼ | ����Ŀ¼ | ������� | �߼����� << | >>
����, ���ӿ�, ��ѧ��, ղ����*
�������պ����ѧ ���տ�ѧ�빤��ѧԺ, ���� 100083
Influence of empennage on flow over upswept after-body
Huang Tao, Wang Yankui, Deng Xueying, Zhan Huiling*
School of Aeronautic Science and Technology, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

Download: PDF (2637KB)   HTML 1KB   Export: BibTeX or EndNote (RIS)      Supporting Info
ժҪ ��1.5?m���ٷ綴�в��ñ�������������/����Ƭ����ʾ�Ͳ���������ʵ�鷽����2��������ֺ�����������ͺ��������Խ������о�.ʵ��ķ���Ϊ40?m/s,��ŵ��Ϊ1.191×105,ӭ�Ƿ�ΧΪ-10°~20°.ʵ��������:����ӭ���ɸ������ı仯,2�ֲ���ģ�ͺ����������������Ϸ���—�޷���—�·������͵ı仯,������������ʽ���벢��β����ʼ�����չ;Сӭ����2�ֲ���ģ�ͺ��������IJ����Ҫ��β���Ħ����������,���ϴ�ӭ����β���������������ѹ����������Ҫ����;��β������ӭ�����Ӷ����ϼ���,�Ӷ���������ʽ���ֺ���������ӭ�DZ仯����Ϊ�ǶԳ�.
Email Alert
�ؼ����� ���ú���   ����   ������ʾ   ����   ��������     
Abstract�� To provide a foundation of upswept after fuselage drag reduction, the flow patterns and aerodynamic characteristics over two upswept rear fuselages with and without empennages were investigated in a 1.5 by 1.5 meters low speed wind tunnel by the methods of oil flow, smoke wire/laser and force measurement. The results were obtained at 40?m/s and Reynolds number of 1.191×105 at angles of attack ranging from -10° to 20°. With the attack angle increasing from negative to positive, the flow over rear fuselage, which is developed from the end of body to forward, goes through three kinds of open separation mode, namely up-separation, non-separation and down-separation. The drag difference between the after-bodies with and without empennages is due to the friction drag on empennages for non-separation mode and is due to separation on the empennages at higher attack angle. The drag reduction caused by separation weakening on vertical tail results in drag increasing slowly with the increase of the positive attack angle.
Keywords�� civil aviation   fuselages   flow visualization   separation   vortex flow     
Received 2005-07-07;
About author: �� ��(1978-),��,����������,��ʿ��, aerogemini@ase.buaa.edu.cn.
����, ���ӿ�, ��ѧ��, ղ����.β�����������������Ե�Ӱ��[J]  �������պ����ѧѧ��, 2006,V32(06): 645-648
Huang Tao, Wang Yankui, Deng Xueying, Zhan Huiling.Influence of empennage on flow over upswept after-body[J]  JOURNAL OF BEIJING UNIVERSITY OF AERONAUTICS AND A, 2006,V32(06): 645-648
http://bhxb.buaa.edu.cn//CN/     ��     http://bhxb.buaa.edu.cn//CN/Y2006/V32/I06/645
Copyright 2010 by �������պ����ѧѧ��