| 乘波布局高焓激波风洞测热试验研究 |
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| 引用本文： | 王晓朋,张陈安,翟建,王发民,叶正寅.乘波布局高焓激波风洞测热试验研究[J].实验流体力学,2019,33(4):52-57. |
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| 作者姓名： | 王晓朋 张陈安 翟建 王发民 叶正寅 |
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| 作者单位： | 1.西北工业大学 翼型、叶栅空气动力学国防科技重点实验室, 西安 710072 |
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| 基金项目： | 中国科学院战略性先导专项XDA17030100 |
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| 摘 要： | 以钝化锥导乘波体为研究对象，开展了高焓激波风洞测热试验以及高温化学非平衡气动加热数值验证，对乘波布局滑翔飞行器前缘线和下壁面热流分布特征进行了研究。结果表明:乘波布局飞行器表面热流主要集中于头部驻点及其附近的前缘小范围区域内；在0°~6°的迎角范围内，迎角的改变基本不会对前缘线热流产生太大影响，但会导致下壁面热流明显增加；而侧滑角即使在0°~4°的范围内变化，也将导致前缘线迎风一侧热流明显增加。
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| 关 键 词： | 乘波体 真实气体效应 气动加热 高焓风洞试验 数值计算 |
| 收稿时间： | 2019-06-24 |
Experimental study on the aero-heating characteristics of waverider in the high enthalpy shock wave tunnel |
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| Institution: | 1.National Key Laboratory of Aerodynamic Design and Research, Northwestern Polytechnical University, Xi'an 710072, China2.State Key Laboratory of High-Temperature Gas Dynamics, Institute of Mechanics, Chinese Academy of Sciences, Beijing 100190, China |
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| Abstract: | Long-range aerodynamic heating is a key scientific problem. In this paper, the cone-derived waverider is designed firstly and then the characteristics of the heat flux distribution along the leading edge and on the lower surface of the waverider are studied by means of the high enthalpy wind tunnel test and the high temperature chemical non-equilibrium aerodynamic heating numerical calculation. Results show that:The high heat flux mainly concentrates on the small region around the stagnation point and the change of angle of attack (0°~6°) does not have an obvious effect on the high heat flux region at the leading edge, but it induces a significant increase of the heat flux on the lower surface. In addition, the change of the sideslip angle (0°~4°) has a significant effect on the heat flux at the leading edge, so it is not recommended to fly with a large sideslip angle. |
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