| 激波风洞中三角翼体模型的大攻角气动力测量和局部方法的应用 |
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| 引用本文： | 马家欢,沈青,陈素贞,潘文欣.激波风洞中三角翼体模型的大攻角气动力测量和局部方法的应用[J].实验流体力学,1993(3). |
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| 作者姓名： | 马家欢 沈青 陈素贞 潘文欣 |
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| 作者单位： | 中国科学院力学研究所
(马家欢，沈青，陈素贞)，中国科学院力学研究所(潘文欣) |
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| 摘 要： | 在激波管风洞中,模型自由飞方法测量了两种不同迎风面三角翼体模型的大攻角气动力。应用局部方法以一种迎风面外形的实验结果为依据,估算了另一迎风面外形的气动特性,结果与实验值吻合较好。另外,本文还进一步估算了航天飞机外形的气动特性,与美国的 CALSPAN 公司48英寸(1.2米)激波风洞中的实验值相比,结果也令人满意。从而表明,局部方法和实验相结合。用于简捷快速估算任意外形的高超声速气动特性是一有效的工程预示方法。
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| 关 键 词： | 激波管风洞 气动力测量 局部方法 模型自由飞 三角翼体模型 |
AERODYNAMIC FORCES MEASUREMENTS OF A DELTA WINGED BODY IN SHOCK TUNNEL AND THE APPLICATION OF LOCAL METHOD |
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| Ma Jiahuan,Shen Qin,Chen Suzhen,Pan Wenxin.AERODYNAMIC FORCES MEASUREMENTS OF A DELTA WINGED BODY IN SHOCK TUNNEL AND THE APPLICATION OF LOCAL METHOD[J].Experiments and Measur in Fluid Mechanics,1993(3). |
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| Authors: | Ma Jiahuan Shen Qin Chen Suzhen Pan Wenxin |
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| Abstract: | Aerodynamic forces of Delta winged body with high angleof attack in two different windward configurations were measured byfree flight method in shock tunnel.The local method with the regimecoefficients derived from shock tunnel experimental results for oneconfiguration was applied to predicting the aerodynamic force coeffi-cients for the another configuration.The prediction agrees reasonably wellwith the experimental results Furthermore,the aerodynamic forcesprediction of space shuttle orbiter model by the local method also showsgood agreement with CALSPAN experimental results. |
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| Keywords: | shock tunnel aerodynamic forces measurement local method model free flight delta winged body |
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