【摘要】 采用轴对称NS方程,数值研究不同热化学非平衡模型对高超声速喷管流场的影响,包括:(1)不同组元数的高温空气模型(5组元、7组元1、1组元)的比较;(2)热力非平衡(双温度)的化学动力过程与热力平衡(单温度)的化学动力过程的比较。计算结果表明,高焓风洞实验条件下喷管流场处于热力和化学都是非平衡的状态。在计算条件下,数值模拟以采用7组元或11组元的热化学非平衡模型为宜。更多还原

【Abstract】 Using axisymmetric full Navier-Stokes equations,the effects of different thermo-chemical nonequilibrium air models on the hypersonic nozzle flow are analyzed numerically.They include(1) the comparision of different high temperature air models(5 species,7 species and 11 species);(2) the comparision of chemical nonequilibrium flow with thermo-nonequilibrium(two temperature model) and thermo-equilibrium(one temperature model).The results show that the flow tends to be in thermo and chemical frozen not far from throat.7 species or 11 species thermochemical nonequilibrium model should be taken for such situation.更多还原