Rapid supersonic performance prediction for 2D ramjet inlets
Rapid supersonic performance prediction for 2D ramjet inlets
复制标题
DOI：
10.1016/j.ast.2016.03.025
复制
发表时间：
2016-06
影响因子：
5.6
通讯作者：
W. Xie;Yan Ge;Chen Hao;Wen Yufen;Shengmin Guo
中科院分区：
文献类型：
--
作者：
W. Xie;Yan Ge;Chen Hao;Wen Yufen;Shengmin Guo
提出了一种快速估算二维冲压发动机进气道质量平均喉道性能的计算工具。基于特征线法，加上对与冲压发动机进气道相关的粘性流动和激波干扰的独特修正，实现了对进气道的准确预测。与粘性计算流体力学模拟结果相比，在典型冲压发动机进气道自由流马赫数为2.2~4.0，相对喉道高度为0.12~0.20，自由流雷诺数为3.20E+5~1.25E+7的工作范围内，该快速预测工具的绝对误差小于3.5%。
A computational tool for quick estimation of mass-averaged throat performance for 2D ramjet inlets is presented. Based on the method of characteristics, coupled with unique corrections to the viscous flow and shock interactions associated with ramjet inlets, accurate predictions for the inlet throat are achieved. In comparison to viscous computational fluid dynamics simulation results, the absolute error for this rapid predictive tool is less than 3.5% over the working range of typical ramjet inlets, where the free-stream Mach number ranges from 2.2 to 4.0; the relative throat height ranges from 0.12 to 0.20, and the free-stream Reynolds number ranges from 3.20E+5 to 1.25E+7.