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首页> 外文会议>ASME turbo expo: turbomachinery technical conference and exposition >DRAG AND HEAT REDUCTION MECHANISM OF THE POROUS OPPOSING JET FOR VARIABLE BLUNT HYPERSONIC VEHICLES
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DRAG AND HEAT REDUCTION MECHANISM OF THE POROUS OPPOSING JET FOR VARIABLE BLUNT HYPERSONIC VEHICLES

机译：可变钝性超音速车辆的多孔对置射流的减阻机理

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Opposing jet, as one of the most practical strategies to achieve the drag and heat reduction, is usually adopted to improve the aerodynamics and the aerothermodynamics of hypersonic vehicles. The porous jet strategy which is suitable for the blunt hypersonic vehicle has been proposed and investigated numerically in this study. The full Navier-Stokes equations and SST k-w turbulence model is used to obtain the flow field properties. The numerical method is validated by the wind tunnel experimental data. This work shows that the porous opposing jet is able to reduce the drag and the aero-heating of blunt hypersonic vehicles. The aerodynamic performance can be improved further by combining the porous jet design with variable blunt methods. When the number of jet orifices (N) is an odd number, the area of Mach disk and the off-distance of Shock wave decrease with the increase in N. When N is an even number, the high temperature region will decrease with the increase in N. The drag reduction ratio increases with the increase of jet orifices when N is an odd number. However, the trend is contrary when N is even. Moreover, when N is odd, the effect of drag reduction is better than that when N is even. Considering both factors of the drag reduction and thermal protection, the porous jet design is useful in improving the overall performance of the blunt hypersonic vehicle. The porous jet has three-dimensional effect, so there exists the optimal injection scheme. The three factors (the number, the spacing and the radius of injection orifices) have a multi-objective optimal solution. It is thus then the drag reduction and the heat protection of the porous jet injection has the best performance.
机译：通常采用相反的喷射，作为实现阻力和散热的最实际的策略之一，通常采用来改善超音速车辆的空气动力学和空气流体动力学。在本研究中，已经提出并在数值上进行了适用于钝的高超声速载体的多孔喷射策略。 Full Navier-Stokes方程和SSTK-W湍流模型用于获得流场属性。用风洞实验数据验证数值方法。这项工作表明，多孔相对的喷射能够减少钝的高超声速车辆的阻力和空气加热。通过将多孔喷射设计与可变钝化方法组合，可以进一步提高空气动力学性能。当喷射孔（n）的数量是奇数时，Mach盘的面积和冲击波的偏移随着N的增加而减小。当n是偶数时，高温区域将随着增加而降低在N.当N是奇数时，阻力减少比率随着喷射孔的增加而增加。然而，当N是偶数时，趋势是相反的。此外，当n是奇数时，减阻的效果比n均匀的效果更好。考虑到减压和热保护的两种因素，多孔喷射设计可用于提高钝性超声波施工的整体性能。多孔喷射具有三维效果，因此存在最佳的注射方案。三个因素（数量，间隔和注射孔半径）具有多目标最佳解决方案。因此，多孔喷射注射的减阻和热保护具有最佳性能。

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