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| 楔—后掠柱激波干扰流场和热流的工程算法 | |
| 引用本文： | 白菡尘 杨茂昭. 楔—后掠柱激波干扰流场和热流的工程算法[J]. 空气动力学学报, 1993, 11(2): 224-231 |
| 作者姓名： | 白菡尘 杨茂昭 |
| 作者单位： | 中国空气动力研究与发展中心，中国空气动力研究与发展中心，中国空气动力研究与发展中心，中国空气动力研究与发展中心 四川绵阳 621000，四川绵阳 621000，四川绵阳 621000，四川绵阳 621000 |
| 摘 要： | 本文针对航天飞机机翼前缘的简化模型,即楔-后掠柱模型,在大后掠、高超声速条件下,提供了一种计算柱体前缘激波干扰流场和热流的工程计算方法。在中国科技大学流体力学实验室的激波风洞中取得了激波干扰的流场显示结果。计算的结果与国内外实验数据的比较表明,这是一种有效的方法。 |
| 关 键 词： | 激波干扰 机翼前缘流场 航天飞机 |
An Engineering Method to Calculate the Interaction Flowfield and Heating on a Wedge- Swept-Cylinder Configuration |
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| Bai Hanchen Huang Zhicheng Yang Maozhao Zhu Qifeng. An Engineering Method to Calculate the Interaction Flowfield and Heating on a Wedge- Swept-Cylinder Configuration[J]. Acta Aerodynamica Sinica, 1993, 11(2): 224-231 | |
| Authors: | Bai Hanchen Huang Zhicheng Yang Maozhao Zhu Qifeng |
| Affiliation: | China Aerodynamics Research and Development Center |
| Abstract: | This paper provides an engineering method to calculate shock interaction flowfield and heating rate along the cylinder leading-edge of a wedge-swept-cylinder configuration, which simulated a highly swept wing leading edge of spaccshuttle at hypersonic flow. The interference flowfield schlieren photographs have been obtained in the shock tube of Lab of Fluid Mechanics of the Univercity of Science and Technology of China, The comparison between calculated results and experimental data indicates that this method is more effective than those at home and abroad. |
| Keywords: | shock interaction wing leading-edge flowfield interference heating rate spaceshuttle. |
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