Rapid supersonic performance prediction for 2D ramjet inlets
Document Type
Article
Publication Date
6-1-2016
Abstract
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.
Publication Source (Journal or Book title)
Aerospace Science and Technology
First Page
220
Last Page
231
Recommended Citation
Xie, W., Ge, Y., Chen, H., Wen, Y., & Guo, S. (2016). Rapid supersonic performance prediction for 2D ramjet inlets. Aerospace Science and Technology, 53, 220-231. https://doi.org/10.1016/j.ast.2016.03.025