Simulation and verification of supersonic axisymetric H2-O2 ignition

• Main Authors: hsu sheng hsiang, 徐勝翔
• Other Authors: 楊一龍
• Format: Others
• Language: zh-TW
• Published: 2005
• Online Access: http://ndltd.ncl.edu.tw/handle/55762833400120491170

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 algorithm. Three difference chemical kinetic schemes, global 2-step, seven species 7-step, and seven species 8-step were used. The solutions show that seven species 7-step and seven species 8-step are very similar. However, the solution of the global 2-step chemical kinetic provides very little reaction, as suggested try previous researchers. The current numerical prediction gives the ignition position at 12.7 D downstream. However, the experimental result shows an ignition position at 8.25 D downstream. The current H2O formation region is also thinner than the region form experimental measurement. Modification of the inlet pressure, inlet Mach number, artificial viscosity, and grid mesh does not alter the current simulation.