Simulation and verification of supersonic axisymetric H2-O2 ignition
碩士 === 中華大學 === 機械與航太工程研究所 === 93 === Axisymetric Navier-Stoke equations coupled with chemical kinetic equations were used to solve the supersonic H2-O2 combustion solutions. The numerical scheme is based on central difference with Jameson’s artificial viscosity, 4-stage Runge-Kutta time marching al...
| Main Authors: | , |
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| Other Authors: | |
| Format: | Others |
| Language: | zh-TW |
| Published: |
2005
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| Online Access: | http://ndltd.ncl.edu.tw/handle/55762833400120491170 |