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�������պ����ѧѧ�� 2011, Vol. 37 Issue (6) :685-689,694    DOI:
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Numerical analysis of high-temperature-gas wind tunnel thermal characteristics
Yao Feng, Dong Sujun, Wang Jun*
School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

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Abstract�� An experimental method using subsonic high-temperature gas flow to simulate aerodynamic thermal environment of near space hypersonic vehicle was introduced. In the test section of the experiment equipment, the room temperatwe air was ejected by the subsonic high-temperature gas flow to make the heat distribution of the experimental condition in line with that of the real flight condition on the cap. 13 experimental conditions were analyzed using computational fluid dynamics(CFD). The numerical analysis verifies the feasibility of the experimental method and provides basis for demonstration of the experiment facilities.
Keywords�� near space   thermal environment   hypersonic aricraft   high-temperature-gas   numerical simulation     
Received 2010-03-10;
About author: Ҧ ��(1982-),��,ɽ��̩ɽ��,��ʿ��,yaofeng 5372@163.com.
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Ҧ��, ���ؾ�, ����.����ȼ���綴�������Է������[J]  �������պ����ѧѧ��, 2011,V37(6): 685-689,694
Yao Feng, Dong Sujun, Wang Jun.Numerical analysis of high-temperature-gas wind tunnel thermal characteristics[J]  JOURNAL OF BEIJING UNIVERSITY OF AERONAUTICS AND A, 2011,V37(6): 685-689,694
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