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以24°压缩拐角为流场模型,针对不同注入总压微射流作用下来流马赫数为2.9的超声速压缩拐角流场进行了数值研究,喷射方向与来流垂直。研究表明,微射流阻挡作用下,其下游速度被减小,而减弱了分离激波强度。此外,微射流与来流耦合会产生正反向旋转流向涡对,在其下洗作用下,高能量流体被带入到边界层底部近壁面处,使此处低能流体被激活,进而增强了边界层的抗逆压能力不易发生分离,且这种激活能力会随注入总压的增加而增强。权衡控制效果和注入能量认为,注入压比(注入总压/来流总压)为0.60的微射流为最优方案,在其作用下,拐角区分离面积被减小了近70%、激波交汇点与壁面的距离被降低了近37%、分离激波强度被削弱近12%。
Taking the corner of 24 ° compression as the flow field model, a numerical study was carried out for the flow field of supersonic compression corner with a flow Mach number of 2.9 under the condition of different total injected micro-jet pressure. The jet direction was perpendicular to the incoming flow. The results show that, under the effect of micro-jet flow blocking, the downstream velocity is reduced and the intensity of the separation shock is weakened. In addition, the micro-jet coupled with the incoming flow will produce positive and negative rotating vortices, and under its action of washing, the high-energy fluid is brought into the bottom near the wall of the boundary layer to activate the low-energy fluid and enhance the The anti-stress ability of the boundary layer is not easy to separate, and this activation ability will increase with the increase of the total pressure injected. Weighing the control effect and the injection energy, it is considered that the micro jet with injection pressure ratio (total pressure injected / total pressure of inflow) is 0.60 is the optimal solution. Under its action, the separation area in the corner area is reduced by nearly 70% The distance between the junction and the wall is reduced by nearly 37% and the separation shock strength is reduced by nearly 12%.