SHOCK WAVE INDUCED UNSTEADY DRAG OVER TWO-DIMENSIONAL CIRCULAR CYLINDER IN AIR
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摘要: 激波管是一种具有结构简单、参数可调范围大和使用方便等特点的气体动力学试验装置。因此,它在跨声速和超声速流的实验研究中得以广泛地应用。但由于激波管中气流的持续时间很短(通常为毫秒量级),所以在激波管中直接测量试验模型上的压力分布等气动参数将是十分困难的。本文利用马赫-曾德干涉仪在激波管中拍摄出激波在二维圆柱上的绕射和反射时的干涉图,直接给出了整个流场的密度分布。再由波后气流满足等熵关系式,可以计算得到流场的压力分布和非定常阻力的大小。Abstract: A shock tube can be used as a convenient aerodynamic testing facility. Thus it was extensively applied to experimental research of transonic and hypersonic flow. However, due to its very short working time quantitative flow measurement such as pressure distribution around a model installed in the shock tube is very difficult. This paper reports the results of unsteady pressure distribution and unsteady drag measurement over circular cylinder installed in a 50mm × 200mm shock tube equipped with Mach-Zehnder ...
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Key words:
- unsteady drag /
- pressure dis-\'ibution /
- Mach-Zehnder interferometer /
- isentro-pic equation /
- isopycnics
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