本文从化学非平衡粘性激波层控制方程出发，用数值法计算了高超音速钝体绕流头部区流场(包括驻点线和音速线)。
In this paper, the nonequilibrium viscous shock layer equations have been used to calculate the hypersonic flows over blunt bodies in the fore-body region (including stagnation line and sonic line).
在热化学非平衡流情况下，经典的粘性相互作用参数和经验公式具有局限性。
The classical viscous interaction parameter and experiential formulae are limitative in thermochemical nonequilibrium flow.
平行切变流的临界层一般分为三类：粘性临界层、非线性临界层和非定常临界层。
The critical layers of waves in parallel shear flow are generally classified into three kinds: viscosity critical layer, nonlinear critical layer, and non-steady critical layer.
针对某静止环形叶栅的激励实验工作，相应的对扩压叶栅进行了不同气流攻角和激励频率的非定常粘性计算与流场分析。
In regard to the excitation experiments, time-Accurate numerical stimulation was carried out to investigate the upstream disturbance frequency effect under different incidence in an annular cascade.
采用单、双温度模型两种粘性激波层方程组对弹头驻点区非平衡流场作了数值模拟。
The numerical solutions of VSL equation sets in one-temperature and two-temperature cases are obtained for flows in the stagnation region of a hypervelocity blunt body.
给出了基于非结构化网格数值求解二维粘性湍流分离流场的压力修正算法。
A pressure correction algorithm was taken out to solve 2d viscous turbulent flow field.
给出了基于非结构化网格数值求解二维粘性湍流分离流场的压力修正算法。
A pressure correction algorithm was taken out to solve 2d viscous turbulent flow field.
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