Laminar-to-turbulent transition onset prediction of hypersonic flows based on laminar kinetic energy equation
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摘要: 通过求解基于稳定性理论的非湍流脉动动能输运方程,预测了来流Ma为5.91的裙锥绕流流动的层流-湍流转捩点,并采用SST(Shear-Stress Transport)湍流模型结合代数间歇因子模型对转捩流场进行了数值模拟.结果表明非湍流脉动动能输运方程模型可以很好地捕捉逆压梯度对转捩前期边界层内的不稳定波动频率的影响.等温壁面条件下计算得到的转捩位置与静风洞实验结果基本一致.壁面冷却促进第2模态不稳定波动的增长,使转捩提前发生.代数间歇因子模型模拟高马赫数流动的转捩区长度较短,温度峰值偏低.Abstract: Onset locations of laminar-to-turbulent transition were predicted for flared-cones with freestream Ma of 5.91 by solving a laminar kinetic energy transport equation based on the linear stability theory numerically. The transitional flowfields were simulated by employing the shear-stress transport(SST) turbulence model, in conjunction with an algebraic intermittency model. Numerical results demonstrate that the current laminar kinetic energy transport equation is capable of predicting the frequencies of unstable disturbances under adverse pressure gradients. The computed transition onset locations of adiabatic wall are in good agreement with experiment data measured from the quiet wind tunnels. Wall cooling promotes the growth of second mode instability, and transition occurs earlier. The length of the transitional zone and temperature peak value are not adequate when the algebraic intermittency model is employed.
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Key words:
- laminar kinetic energy /
- transition prediction /
- quiet wind tunnel
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