In this work, near-infrared and ultraviolet spectroscopic data collected during the Hayabusa spacecraft reentry is used as the basis for validating numerical and experimental studies using the compressible flow computational fluid dynamics code Eilmer3 and the University of Queensland’s X2 expansion tube. Spectra generated numerically from simulations of the full-scale vehicle at the selected trajectory point at 1 s after peak total heating were compared with experimentally captured spectra over a binary-scaled and total-enthalpy-matched radiating shock layer around a 1/5-scale Hayabusa model, and both sets of data were compared with spectra obtained from flight. For the infrared results, experimental and simulated spectra, as well as simulated and flight spectra, compared well within an uncertainty margin of between 20 and 90% depending on the particular case being compared. Experimental and simulated ultraviolet results did not compare well; however, comparisons between simulated and flight ultraviolet spectra were more favorable, comparing well within an uncertainty of around 50%.

在这项工作中，隼鸟号航天器再入期间收集的近红外和紫外光谱数据被用作使用可压缩流计算流体动力学代码Eilmer3验证数值和实验研究的基础和昆士兰大学的X2膨胀管。将在峰值总加热后 1 秒时在选定轨迹点模拟全尺寸车辆以数值方式生成的光谱与在 1/5 尺度周围的二进制和总焓匹配辐射冲击层上实验捕获的光谱进行比较Hayabusa 模型，并将两组数据与从飞行中获得的光谱进行比较。对于红外结果，实验和模拟光谱，以及模拟和飞行光谱，根据所比较的特定情况，在 20% 到 90% 的不确定性范围内进行了很好的比较。实验和模拟紫外线结果没有很好的比较；然而，模拟和飞行紫外光谱之间的比较更有利，在大约 50% 的不确定性内进行比较。