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2018 Joint Thermophysics and Heat Transfer Conference最新文献

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Thermal Cycle Testing of Titanium Superhydrophobic Surfaces for a Spacecraft Jumping Droplet Thermal Diode 航天器跳液滴热二极管用钛超疏水表面热循环试验
Pub Date : 2018-06-24 DOI: 10.2514/6.2018-2946
J. Supowit, Christopher H. Baker, Bailey Zhao, John P. McHale, Ryan Miller, P. Pichardo, C. Zuhlke, Nicholas Roth, A. Tsubaki, Mahdi Mohammadi-Ghaleni, S. Nejati, D. Alexander
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引用次数: 3
A Numerical Model of the Blade Element Momentum Method for Rotating Airfoils with Heat Transfer Calculation 旋转翼型叶片单元动量法的数值模型及传热计算
Pub Date : 2018-06-24 DOI: 10.2514/6.2018-4077
A. Samad, F. Morency, C. Volat
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引用次数: 1
Asymmetric Thermal Transport by Adjusting Structural Defects 调整结构缺陷的不对称热传递
Pub Date : 2018-06-24 DOI: 10.2514/6.2018-2949
A. Nobakht, Seunghan Shin, Jiaqi Wang
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引用次数: 0
Aerothermodynamic Shape Optimization of Reentry Capsule 返回舱气动外形优化
Pub Date : 2018-06-24 DOI: 10.2514/6.2018-4071
H. Kutkan, S. Eyi
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引用次数: 1
Comparison of Different Approaches for Numerical Simulation of High Enthalpy Flows at Thermochemical Equilibrium 热化学平衡高焓流数值模拟不同方法的比较
Pub Date : 2018-06-24 DOI: 10.2514/6.2018-3269
A. Diwakar, Veda Krishna Vyas Ramasahayam, K. Bodi
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引用次数: 0
Radiative Heating Prediction of Hyper-Velocity Re-entry Vehicles based on Finite Volume Method 基于有限体积法的超高速再入飞行器辐射加热预测
Pub Date : 2018-06-24 DOI: 10.2514/6.2018-4076
J. Lyu, Jingke Hao, Wenbo Miao, Xiaoli Cheng, Jijun Yu
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引用次数: 0
Calculation of the Spectral Hemispherical Emissivity of an Arbitrarily Orientated Uniaxial Crystal 任意取向单轴晶体光谱半球发射率的计算
Pub Date : 2018-06-24 DOI: 10.2514/6.2018-4075
Xiaohu Wu, C. Fu, Zhuomin M. Zhang
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引用次数: 0
One-dimensional modeling methodology for shock tubes: Application to the EAST facility 激波管一维建模方法:在EAST设施中的应用
Pub Date : 2018-06-24 DOI: 10.2514/6.2018-4181
M. Priyadarshini, A. Munafò, A. Brandis, B. Cruden, M. Panesi
In this work, a one-dimensional methodology for simulating shock tubes is developed. The model accounts for the viscous interactions of the shock with the shock tube wall by adding an area change source term in the 1-D conservation equations corresponding to the boundary layer growth. This source term corresponds to the mass and energy going into the boundary layer. The boundary layer growth is computed using a simple model with a scaling factor. This scale factor is used to tailor a solution to match the deceleration profile of a shock tube test. In doing so, not only will the source term take into account boundary layer losses, it will also cover any effect due to radiative cooling loses from the gas. For this study, the Electric Arc Shock Tube(EAST) facility at NASA Ames Research Center is modeled for Earth reentry conditions. The purpose of this paper is to investigate if anomalies identified for certain conditions in the EAST data are due to shock deceleration. These anomalies include measuring electron number density above equilibrium predictions and observing that radiance profiles can continually increase behind the shock, never reaching steady state, for certain shots (typically those less than 10 km/s). An eleven species air mixture is chosen to study the chemistry of the flow. Comparisons of the simulations to the experimental results are presented. Good agreement with the shock deceleration profiles was achieved by tuning in the boundary layer scale factor. The temperature as well as electron number density increases behind the shock, as has also been observed in the experiments. Finally, radiance comparisons between results from NEQAIR and experiments also show good agreement for some shots, but significant discrepancies are still observed for others. shows that the experiments record an increase in the radiation behind the shock which is captured by the viscous simulation. This increase in radiance is due to the fact that the temperature behind the shock front increases as the gas further away from the shock was shocked at a higher velocity. In the IR region, there is no steady state radiance as can be seen from the figures. Hence, using this model can potentially provide an avenue to understand the data obtained from the experiments. There is a dramatic increase in the radiance in the IR region when compared to the UV region in the EAST data which is also observed in the simulations. The radiance data in the VUV region shows that it is steady. The simulations show radiance increase in this region as well.
在这项工作中,开发了一种一维激波管模拟方法。该模型通过在边界层生长对应的一维守恒方程中加入面积变化源项来解释激波与激波管壁的粘性相互作用。这个源项对应于进入边界层的质量和能量。边界层的生长是用一个带有比例因子的简单模型来计算的。该比例因子用于定制解决方案,以匹配激波管试验的减速剖面。这样一来,源项不仅将边界层损失考虑在内,而且还将涵盖由于气体的辐射冷却损失而产生的任何影响。在这项研究中,美国宇航局艾姆斯研究中心的电弧激波管(EAST)设施模拟了地球再入条件。本文的目的是研究在东方数据中确定的某些条件下的异常是否由于冲击减速。这些异常包括测量高于平衡预测的电子数密度,以及观察到某些射击(通常小于10km /s)的辐射曲线在激波后不断增加,从未达到稳定状态。选择了11种空气混合物来研究流动的化学性质。仿真结果与实验结果进行了比较。通过调整边界层尺度因子,与激波减速度曲线吻合较好。温度和电子数密度在激波后增加,这在实验中也观察到了。最后,NEQAIR和实验结果之间的辐射比较也显示了一些镜头的良好一致性,但仍然观察到其他镜头的显着差异。表明实验记录了激波后辐射的增加,这是由粘性模拟捕获的。辐射的增加是由于当远离激波的气体以更高的速度被激波冲击时,激波锋面后面的温度增加了。从图中可以看出,在红外区域没有稳态辐射。因此,使用这个模型可以潜在地提供一个途径来理解从实验中获得的数据。与东部数据中的紫外区相比,红外区的辐射显著增加,这在模拟中也观察到。VUV区域的辐射度数据表明它是稳定的。模拟结果表明,该区域的辐射增强。
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引用次数: 5
Modeling of Gas-Phase Chemical Kinetics for Pyrolyzing Ablators 热解烧蚀器气相化学动力学建模
Pub Date : 2018-06-24 DOI: 10.2514/6.2018-3274
Samuel Y. Chen, I. Boyd, N. Martin, D. Fletcher
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引用次数: 5
Conjugate Analyses of Ablation in the HIPPO Nozzle HIPPO喷嘴烧蚀的共轭分析
Pub Date : 2018-06-24 DOI: 10.2514/6.2018-3271
Peter G. Cross, I. Boyd
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引用次数: 2
期刊
2018 Joint Thermophysics and Heat Transfer Conference
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