| 跨声速风洞第二喉道性能计算 |
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| 引用本文： | 丛成华,廖达雄,陈吉明,秦红岗.跨声速风洞第二喉道性能计算[J].航空动力学报,2010,25(9):2050-2056. |
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| 作者姓名： | 丛成华 廖达雄 陈吉明 秦红岗 |
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| 作者单位： | 1. 中国空气动力研究与发展中心,空气动力学国家重点实验室,绵阳,621000;中国空气动力研究与发展中心,设备设计及测试技术研究所,绵阳,621000
2. 中国空气动力研究与发展中心,设备设计及测试技术研究所,绵阳,621000 |
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| 基金项目： | 空气动力学国家重点实验室基金(SKLA2009A0208) |
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| 摘 要： | 采用数值方法对跨声速风洞第二喉道性能进行了研究.首先根据第二喉道的一般设计准则,对第二喉道进行了气动设计,然后通过数值模拟对使用调节片和中心体调节第二喉道面积从而对试验段马赫数精确控制的效果进行了研究,结果表明其马赫数控制精度可以达到0.001;最后通过数值模拟对第二喉道气动设计进行了比对校核,并优选出最终设计方案.
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| 关 键 词： | 跨声速风洞 试验段 第二喉道 精确控制 气动设计 |
| 收稿时间： | 2009/8/27 0:00:00 |
| 修稿时间： | 2010/2/10 0:00:00 |
Numerical investigation on performance of second throat in transonic wind tunnel |
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| CONG Cheng-Hu,LIAO Da-Xiong,CHEN Ji-Ming and QIN Hong-Gang.Numerical investigation on performance of second throat in transonic wind tunnel[J].Journal of Aerospace Power,2010,25(9):2050-2056. |
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| Authors: | CONG Cheng-Hu LIAO Da-Xiong CHEN Ji-Ming and QIN Hong-Gang |
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| Institution: | State Key Laboratory of Aerodynamics,China Aerodynamics Research and Development Center,Mianyang 621000,China;Facility Design and Instrumentation Institute,China Aerodynamics Research and Development Center,Mianyang 621000,China;State Key Laboratory of Aerodynamics,China Aerodynamics Research and Development Center,Mianyang 621000,China;Facility Design and Instrumentation Institute,China Aerodynamics Research and Development Center,Mianyang 621000,China;State Key Laboratory of Aerodynamics,China Aerodynamics Research and Development Center,Mianyang 621000,China;Facility Design and Instrumentation Institute,China Aerodynamics Research and Development Center,Mianyang 621000,China;Facility Design and Instrumentation Institute,China Aerodynamics Research and Development Center,Mianyang 621000,China |
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| Abstract: | This paper presented the numerical investigation reports about the performance of transonic wind tunnel's second throat.Firstly,second throats were designed according to the general design rule.Then exact Mach number control was studied by numerical simulation when different second throat areas were analyzed by adjusting wall flaps and center body.The numerical results indicate that the control precision of Mach number is 0.001.At last,different models were studied based on the numerical results,and then the most efficient model was selected. |
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| Keywords: | transonic wind tunnel test section second throat accurately control aerodynamics design |
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