| 几何尺寸对高超声速进气道气动性能的影响 |
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| 引用本文： | 王亚岗,袁化成,郭荣伟. 几何尺寸对高超声速进气道气动性能的影响[J]. 航空学报, 2014, 35(7): 1893-1901. DOI: 10.7527/S1000-6893.2013.0459 |
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| 作者姓名： | 王亚岗 袁化成 郭荣伟 |
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| 作者单位： | 江苏省航空动力系统重点实验室, 南京航空航天大学 能源与动力学院, 江苏 南京 210016 |
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| 摘 要： | 为了探索模型缩尺比对高超声速进气道气动性能的影响，对不同缩尺比的二元高超声速进气道开展了数值模拟研究，结果表明：随着缩尺比的增大，进气道流量系数、隔离段出口总压恢复系数和马赫数均逐渐增大，而静压比逐渐减小，且来流马赫数越高，上述参数变化幅度越大。由理论与数值模拟分析可知，上述现象主要是由于不同缩尺比下，进气道当地雷诺数不同，导致进气道附面层相对厚度变化，进而影响进气道气动性能。理论分析了进气道总压恢复系数与缩尺比的定量关系，就进气道而言，进气道进口处附面层相对厚度减小1%，隔离段出口总压恢复系数提高约0.7%。
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| 关 键 词： | 高超声速进气道 缩尺比 网格划分 数值模拟 附面层相对厚度 总压恢复系数 |
| 收稿时间： | 2013-09-09 |
| 修稿时间： | 2013-11-04 |
Effect of Geometric Dimensions on Aerodynamic Performance of Hypersonic Inlet |
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| WANG Yagang,YUAN Huacheng,GUO Rongwei. Effect of Geometric Dimensions on Aerodynamic Performance of Hypersonic Inlet[J]. Acta Aeronautica et Astronautica Sinica, 2014, 35(7): 1893-1901. DOI: 10.7527/S1000-6893.2013.0459 |
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| Authors: | WANG Yagang YUAN Huacheng GUO Rongwei |
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| Affiliation: | College of Energy and Power, Nanjing University of Aeronautics and Astronautics, Jiangsu Province Key Laboratory of Aerospace Power Systems, Nanjing 210016, China |
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| Abstract: | To investigate the effects of size construction ratio of model on hypersonic inlet's aerodynamic performances, numerical simulation for hypersonic inlet model with different size construction ratios was carried out. The results indicated that as the construction ratio increased, the total-pressure recovery coefficient, Mach number and the mass flow coefficient of inlet isolator's exit all raised while the static pressure ratio declined. And the trend is more apparent at higher free-stream Mach number. Theoretical analysis and numerical simulation show that the illustrated phenomenon is mainly attributed to the change of the relative thickness of boundary layer at different conditional Reynolds numbers. Through the theoretical analysis on the quantitative correlation between the total-pressure recovery coefficient and the size construction ratio, as for the inlet model investigated in this paper, when the relative thickness of boundary layer decreased by 1%, the total pressure recovery coefficient of inlet isolator's exit would increase by about 0.7%. |
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| Keywords: | hypersonic inlet scale ratio grid divisions numerical simulation relative thickness of boundary-layer total-pressure recovery coefficient |
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