Computational simulation of emission spectra from shock-layer flows in an arcjet facility
Computational simulation of emission spectra from shock-layer flows in an arcjet facility
复制标题
电弧喷射装置中激波层流发射光谱的计算模拟
DOI：
10.2514/2.6343
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发表时间：
1998
期刊：
影响因子：
--
通讯作者：
D. Fletcher
中科院分区：
文献类型：
--
作者：
T. Gökçen;C. S. Park;M. Newfield;D. Fletcher
我们报告了在NASA Ames研究中心的高焓弧形喷气发动机风洞中非平衡钝体激波层流动的计算与实验研究的比较。实验数据包括平面圆柱模型前面形成的激波层辐射的空间分辨发射光谱。用多温度非平衡程序计算了锥形喷管流动、超音速喷流和激波层流动。采用视线(LOS)辐射程序从计算的流场中预测光谱。计算的视线发射强度与实验数据直接比较，沿停滞流线的几个轴向位置。从实验光谱中推导出各种LOS平均流动特性，如振动温度、旋转温度和物种数密度，并与计算结果进行了比较。通过比较，评估了弧喷激波层中的热化学平衡过程。
We report computational comparisons with experimental studies of a nonequilibrium blunt-body shock-layer flow in a high-enthalpy arcjet wind tunnel at NASA Ames Research Center. The experimental data include spatially resolved emission spectra of radiation emanating from a shock layer formed in front of a flat-faced cylinder model. Multitemperature nonequilibrium codes are used to compute the conical nozzle flow, supersonic jet, and shock-layer flow. A line-of-sight (LOS) radiation code is employed to predict the spectra from the computed flowfield. Computed LOS emission intensities are directly compared with the experimental data at several axial locations along the stagnation streamline. Various LOS-averaged flow properties, such as vibrational and rotational temperatures, and species number densities, deduced from the experimental spectra, are compared with computed results. Comparisons provide an assessment of thermochemical equilibration processes in an arcjet shock layer