[an error occurred while processing this directive]
���¿��ټ��� �߼�����
   ��ҳ  �ڿ�����  ��ί��  Ͷ��ָ��  �ڿ�����  ��������  �� �� ��  ��ϵ����
�������պ����ѧѧ�� 2006, Vol. 32 Issue (02) :130-134    DOI:
���� ����Ŀ¼ | ����Ŀ¼ | ������� | �߼����� << | >>
������, ����*
�������պ����ѧ �ѧԺ, ���� 100083
Effects of free stream on flowfield and performance of linear aerospike nozzle
Wang Changhui, Liu Yu*
School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

Download: PDF (513KB)   HTML 1KB   Export: BibTeX or EndNote (RIS)      Supporting Info
ժҪ ���ĸ���ͬ�߶���ѡ���д����Ե����������,����ͶԱ��˲�ͬ��������ʽ������ܵĽ��ͺ���׶�����ѹǿ�ֲ�,��ֵģ���о�����������ʽ������������ܵ�Ӱ��.�������,������ɵ�������ʧ��Ҫ�������������ײ��������Ӻ���׶����ѹǿ����������.���еͿ�����,�������ײ���������׶����������������������Ӷ���С,���������������ܵ�Ӱ����߶ȵ����Ӷ�����,�ӵ�����Ƶ��ijһ�߶ȿ�ʼ��׶��������������Ӱ��.�����������������ʱ,������ʧ����������������ӳɽ�����������;����������ʱ,������ʧͻȻ���ֽϴ��������;�ڼ����ij����ٷ�Χ��,������ʧ���������������ֻ��С������.
Email Alert
�ؼ����� ���������   ���ܷ���   ��ʽ���   ����     
Abstract�� Numerical studies on effects of free stream on flowfield and performance of aerospike nozzle were presented. Aerospike nozzle performance losses and pressure distribution along plug surface were computed and compared at four different altitudes with typical free stream Mach numbers. It is shown that aerospike nozzle performance losses caused by free stream primarily result from increase of lift body base drag and decrease of plug pressure distribution. At mid and low altitudes, thrust of lift body base and plug ramp decreases with increasing free stream Mach number. The effects of free stream on performance decrease with increasing altitude, and from a certain altitude lower than design point thrust of plug ramp is not influenced by the free stream any more. For subsonic free stream, performance losses almost linearly increase with increasing Mach number. For transonic free stream, sudden performance degradation occurs. For the further supersonic range, performance losses increase slightly with increasing Mach number.
Keywords�� rocket engines   performance analysis   aerospike nozzle   free stream     
Received 2004-12-10;


About author: ������(1977-),��,�����̽���,��ʿ��, wangchanghui@buaa.edu.cn.
������, ����.��������ʽ������������ܵ�Ӱ��[J]  �������պ����ѧѧ��, 2006,V32(02): 130-134
Wang Changhui, Liu Yu.Effects of free stream on flowfield and performance of linear aerospike nozzle[J]  JOURNAL OF BEIJING UNIVERSITY OF AERONAUTICS AND A, 2006,V32(02): 130-134
http://bhxb.buaa.edu.cn//CN/     ��     http://bhxb.buaa.edu.cn//CN/Y2006/V32/I02/130
Copyright 2010 by �������պ����ѧѧ��