Three-dimensional analysis of scramjet nozzle flows
Three-dimensional analysis of scramjet nozzle flows
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DOI：
10.2514/3.23806
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发表时间：
1993-11
影响因子：
1.9
通讯作者：
T. Ishiguro;R. Takaki;T. Mitani;T. Hiraiwa
中科院分区：
文献类型：
--
作者：
T. Ishiguro;R. Takaki;T. Mitani;T. Hiraiwa
对某型面状喷管的性能进行了数值计算和实验对比。采用全Navier-Stokes方程和Baldwin-Lomax湍流模型对三维喷管流场进行数值求解。使用测量的压力和热流分布进行了代码验证研究。研究了过膨胀条件下分离激波与主内流的相互作用。在超燃冲压发动机喷管中，这种相互作用产生的性能比假定二维分离时估计的性能要高。评价了喷管内流损失和过膨胀损失。
Numerical and experimental results of performance in National Aero-Space Plane-like nozzles are compared. The full Navier-Stokes equation with the Baldwin-Lomax turbulence model was adopted to solve the threedimensional nozzle flows. A code validation study was conducted using pressure and heat-flux distributions measured. The interactions of separation shocks with the main internal flow under overexpanded conditions were investigated. The interaction yields higher performance in scramjet nozzles than that estimated assuming a two-dimensional separation. The losses in the nozzle internal flow and the overexpansion loss were evaluated.