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将SST(shear stress transport)和TNT(turbulent/non-turbulent)湍流模型输运方程与平均流场控制方程进行隐式紧耦合求解,结合当地时间步长方法和湍流源项隐式处理确保求解过程的快速和稳定.采用AUSMPW+(AUSM by pressure-based weight functions)格式和LU-SGS(lower-upper symmetric GaussSeidel)隐式紧耦合方法对高超声速压缩拐角流动、锥柱裙流动和超声速非对称激波/边界层干扰问题进行了数值模拟.计算结果与实验值的对比表明:SST模型和TNT湍流模型可以很好地预测15°压缩拐角流动的壁面压力和热流密度;随着压缩拐角的增大,计算结果与实验值偏差增大;可压缩性修正对压缩拐角流动的压力和热流密度分布有很大影响,对超声速非对称激波/边界层干扰流动影响很小;隐式紧耦合方法比显式紧耦合方法具有更好的收敛特性.
Tensile stress transport (TST) and TNT (turbulent / non-turbulent) turbulence model transport equations are solved implicitly and tightly coupled with the mean flow field control equations. The local time step method and the turbulent source term implicit processing are used to ensure the solution process (AUSM by pressure-based weight functions) format and the LU-SGS (implicit-lower symmetric GaussSeidel) implicit tight coupling method are applied to the hypersonic compression corner flow, cone skirt flow and supersonic asymmetric shock wave / Boundary layer disturbance.The numerical results and experimental results show that the SST model and the TNT turbulence model can well predict the wall pressure and heat flux density in the corner of 15 ° compression. With the increase of compression corner, The calculated results deviate from the experimental values. The compressibility correction has a great influence on the pressure and heat flux density distribution in the compressed corner flow, and has little effect on the supersonic asymmetric shock / boundary layer interference flow. Implicit Tight Coupling Method Tightly coupled methods have better convergence characteristics.