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Effect of adverse pressure gradient on supersonic compressible boundary layer combustion

机译：不利压力梯度对超音速压缩边界层燃烧的影响

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Influences of adverse pressure gradient (APG) on supersonic turbulent boundary layers are numerically studied using Reynolds-averaged Navier-Stokes (RANS) equations. The RANS methodology is validated by comparing the numerical results with the existing experimental data. Although the flame is restricted in the boundary layer, the heat flux is reduced rather than increased for the suppressed turbulence momentum transportation ability. Moreover, APG contributes more to the heat flux than combustion heat release does. Compared with no-injection case, a large skin friction reduction can be obtained by boundary layer combustion, and further reduction can be achieved in APG state. Additionally, the effects of combustion in APG on the velocity laws of the wall show that White's velocity law is close to the numerical results in the outer region of boundary layer, and Nichols's velocity law is appropriate in the whole boundary layer unless the APG is too strong. Turbulence intensity influences are analyzed in the end. Results show that the additional reduction of skin friction due to induced combustion cannot offset the skin friction increase caused by high turbulence intensity. (C) 2019 Elsevier Masson SAS. All rights reserved.
机译：使用Reynolds平均Navier-Stokes（RAN）方程，在数值研究超音速湍流边界层对超音速湍流边界层的影响。通过将数值结果与现有的实验数据进行比较来验证RAN方法。尽管在边界层中限制火焰，但是对于抑制湍流动量运输能力而不是增加热通量而不是增加。此外，APG与燃烧热释放相比的热通量更多地贡献更多。与无注射箱相比，通过边界层燃烧可以获得大的皮肤摩擦减少，并且可以在APG状态下实现进一步的减少。另外，燃烧在APG上对墙体速度定律的影响表明，白色的速度定律接近边界层外部区域的数值结果，除非APG也是如此，否则Nichols的速度定律是合适的强的。最后分析湍流强度影响。结果表明，由于诱导燃烧引起的皮肤摩擦的额外降低不能抵消由高湍流强度引起的皮肤摩擦增加。 （c）2019年Elsevier Masson SAS。版权所有。

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