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首页> 外文期刊>The Aeronautical Journal >Experimental and numerical heat transfer from vortex-injection interaction in scramjet flowfields
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Experimental and numerical heat transfer from vortex-injection interaction in scramjet flowfields

机译：斯普拉克喷射流域涡流注射相互作用的实验性和数值传热

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ABSTRACT Air-breathing propulsion has the potential to decrease the cost per kilogram for access-to-space, while increasing the flexibility of available low earth orbits. However, to meet the performance requirements, fuel-air mixing inside of scramjet engines and thermal management still need to be improved.An option to address these issues is to use intrinsically generated vortices from scramjet inlets to enhance fuel-air mixing further downstream, leading to shorter, less internal drag generating, and thus more efficient engines. Previous works have studied this vortex-injection interaction numerically, but validation was impractical due to lack of published experimental data. This paper extends upon these previous works by providing experimental data for a canonical geometry, obtained in the T4 Stalker Tube at Mach 8 flight conditions, and assesses the accuracy of numerical methodologies such as RANS CFD to predict the vortex-injection interaction.Focus is placed on understanding the ability of the numerical methodology to replicate the most important aspects of the vortex-injection interaction. Results show overall good agreement between the numerical and experimental results, as all major features are captured. However, limitations are encountered, especially due to a localised region of over predicted heat flux.
机译：摘要空气呼吸推进有可能降低每公斤的成本供入住空间，同时增加可用低地球轨道的灵活性。但是，为了满足性能要求，仍需要改善跳闸发动机和热管理内部的燃料 - 空气混合。解决这些问题的选项是使用扰刀入口的本质上产生涡流，以增强进一步下游的燃料空气混合更短，更少的内部拖动生成，因此更有效的引擎。以前的作品在数值上研究了这种涡流注射相互作用，但由于缺乏公布的实验数据，验证是不切实际的。本文通过在马赫8飞行条件下的T4跟踪管中获得的规范几何形式提供实验数据来延伸到这些先前的作品，并评估RAN CFD等数值方法的准确性，以预测涡流注射相互作用。梗塞了解数值方法论复制涡流互动最重要方面的能力。结果显示数值和实验结果之间的总体良好一致，因为所有主要特征都被捕获。然而，遇到限制，特别是由于过度预测的热通量的局部区域。

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