Measurement and numerical simulation of flow field parameters of free flight spheres with flight velocity from 5 to 7 km/s in CO2
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摘要: 为研究火星进入条件下的非平衡流动特性，在中国空气动力研究与发展中心超高速空气动力研究所弹道靶上测量了CO2中针对火星探测器进入速度范围5~7 km/s条件下的自由飞圆球的激波脱体距离。实验数据基于阴影法测量，并将其与数值计算结果进行对比，进一步计算了实验流场温度和组分分布等流场参数。一般认为激波脱体距离随来流速度升高而呈单调减小趋势，但研究结果表明：实验状态下，圆球飞行速度约5.5~7.0 km/s的范围内，圆球激波脱体距离随飞行速度升高而增大；采用Park的双温度非平衡模型和5组分6反应的CO2化学反应动力模型可基本再现本文自由飞圆球激波脱体距离的实验测量数据；根据计算结果推测，本实验状态下自由飞圆球波后靠近激波一侧区域的流场主要处于热化学非平衡状态；当来流速度在约5.5~7.0 km/s的范围内时，流场组分CO开始发生显著离解，是引起圆球激波脱体距离在该速度范围内随速度升高反而增大的可能原因。Abstract: To investigate the nonequilibrium flow characteristics under Mars entry condition, shock standoff distances over free flight spheres with flight velocities from 5 to 7 km/s in CO2 are measured in the ballistic range at Hypervelocity Aerodynamics Institute of China Aerodynamics Research and Development Center (HAI, CARDC). Test data are measured by the shadowgraph and compared with calculated results, based on which the temperature and species profiles of the test flow field are further calculated. Shock standoff distance is generally supposed to decrease monotonously as the free steam velocity increases. However, it is found through the present test results that, the shock standoff distances over spheres actually increase with the increase of the flight velocity from 5.5 to 7.0 km/s. Using Park's two-temperature model and a 5-species 6-reactions chemical reaction model can basically reproduce the measured shock standoff distances of the present test. It is shown from the test results that the flow field shortly after the shock over the spheres is mainly in theromchemical nonequilibrium. The specie CO starts to dissociate at the free stream velocity from 5.5 to 7.0 km/s, which is the possible cause of the increase of the shock standoff distances over spheres within this range of velocity.
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图 1 实验设备和测试系统示意图
Figure 1. Schematic of the arrangement of the test facility and measurement systems
图 5 激波脱体距离实验测量数据随飞行速度变化
Figure 5. Dependence of measured shock standoff distances on the flight velocities
图 7 自由飞圆球激波脱体距离的实验测量数据和数值计算结果对比
Figure 7. Comparison between the measured and calculated shock standoff distances of the free flight spheres
图 8 驻点线平动温度T和振动温度Tvib分布数值计算结果对比
Figure 8. Comparsion of the calcultared translational and vibrational temperature profiles along the stagnation line
图 9 驻点线组分摩尔质量分数分布数值计算结果对比
Figure 9. Comparsion of the calcultared species mole fraction profiles along the stagnation line
图 10 实验0021和实验0025状态下驻点线密度分布数值计算结果对比
Figure 10. Comparison between the calculated density profiles of test 0021 and test 0025
表 1 激波脱体距离实验测量数据和对应实验状态
Table 1. Measured shock standoff distances and corresponding test conditions of present test
编号 模型直径D/mm 靶室温度T0/K 靶室压力p0/kPa 双尺度参数ρR/(kg·m－2) 模型速度V/(km·s－1) 马赫数Ma δ/R测量值 测量误差 0018 6 282.25 10.81 6.08×10－4 5.473 20.8 0.0467 ±4.53% 0021 6 283.15 11.01 6.17×10－4 5.715 21.7 0.0462 ±4.98% 0022 6 282.55 10.99 6.17×10－4 6.603 25.1 0.0538 ±5.20% 0023 6 282.55 10.99 6.17×10－4 6.781 25.7 0.0515 ±5.56% 0024 6 284.65 11.07 6.17×10－4 4.562 17.3 0.0497 ±4.62% 0025 6 285.15 11.08 6.17×10－4 7.314 27.6 0.0520 ±6.21% 
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表 2 双温度模型和5组分6反应模型计算的激波脱体距离与实验数据的偏差
Table 2. Comparison between the measured and calculated shock standoff distances using the two temperature model and 5 species and 6 reactions model
编号 δ/R测量值 测量误差 δ/R计算值 计算值相对测量值偏差 0018 0.0467 ±4.53% 0.0470 0.64% 0021 0.0462 ±4.98% 0.0474 2.60% 0022 0.0538 ±5.20% 0.0547 1.67% 0023 0.0515 ±5.56% 0.0547 6.21% 0024 0.0497 ±4.62% 0.0500 0.60% 0025 0.0520 ±6.21% 0.0557 7.12%
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