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Numerical Studies on Chemical Non-Equilibrium Flow of the Base-Bleed Unit Wake

机译：基排单元尾流化学非平衡流动的数值研究

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摘要

Numerical studies of compressible base flows with base bleed injection as an effective way to control the base flow for the base drag reduction and heat energy addition of axisymmetric projectiles with a boattailed afterbody in supersonic freestream are carried out by considering the base burning process. The idea developed in the study is to obtain the lowest base drag by analyzing the complex fluid dynamic characteristics found in a supersonic base flow field, including combined effects of boattailing and secondary combustion of the wake under different conditions. Overall fluid dynamic and chemical non-equilibrium flow are then simulated by incorporating the H-2-CO combustion model with 12 reaction steps involving eight reactive species (H, H-2, H2O, OH, CO, CO2, O, and O-2) into a NavierStokes computer code. Various base flow and component distribution characteristics are obtained by changing injection parameter I, which is defined as the bleed mass flow rate normalized by the product of the base area and the freestream mass flux, and the bleed temperature. The results obtained through the present study show that, with increasing injection parameter I, the average base pressure is found to increase quickly initially, attain a slow increase near an injection parameter of I = 0.007, and then remain constant with further increase in I. Moreover, based on changing the bleed temperature, the base pressure rises and the heat energy addition as well as mass addition mechanisms associated with base secondary combustion are found to be higher than that without base secondary combustion. The secondary combustion results in a significant increase in flame temperature and changes the product composition, which cannot be ignored, although the chemical kinetics and fluid dynamic will fulfill another important role. Thus, a better effect on base drag reduction as well as base pressure increase can be attained by adopting appropriate injection parameter and bleed temperature.
机译：通过考虑基础燃烧过程，对具有基础放气注入的可压缩基础流进行了数值研究，以此作为控制超音速自由流中带有船尾形尾部的轴对称弹丸基础减阻和热能添加的有效方法。该研究中提出的想法是，通过分析在超音速基础流场中发现的复杂流体动力学特性（包括船尾和尾流在不同条件下的二次燃烧的综合影响）来获得最低的基础阻力。然后，通过将H-2-CO燃烧模型与12个反应步骤（涉及8种反应物（H，H-2，H2O，OH，CO，CO2，O和O- 2）放入NavierStokes计算机代码。通过更改喷射参数I，可以获得各种基本流量和组分分布特性，该参数定义为通过基本面积和自由流质量通量与排放温度的乘积标准化的排放质量流量。通过本研究获得的结果表明，随着注入参数I的增加，发现平均基本压力开始时迅速增加，在I = 0.007的注入参数附近缓慢增加，然后随着I的进一步增加而保持恒定。此外，基于改变放气温度，基础压力升高，并且发现与基础二次燃烧相关的热能添加以及质量添加机制比没有基础二次燃烧的热能添加以及质量添加机制更高。二次燃烧导致火焰温度显着升高，并改变了产品成分，尽管化学动力学和流体动力学将发挥另一重要作用，但是这不能忽略。因此，通过采用适当的喷射参数和排放温度，可以获得对降低基础阻力以及提高基础压力的更好效果。

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