摘要
利用发射燃气动力学三维仿真手段研究了双面导流器排导燃气的基本规律。仿真研究表明,燃气流经双面导流器呈蝶形排导规律;受双面导流器顶端干扰,燃气流在双面导流器顶端附近形成帽形脱体激波,并在双面导流器顶端形成驼峰效应;同时,由于受双面导流器及射流自身结构影响,在双面导流器腹部形成二次压缩激波和核状流元结构。在仿真研究基础上,开展的燃气喷流试验验证了双面导流器排导规律。
The deflecting features of the double-faced deflector have been demonstrated by three-dimensional dynamical simulation of combustion-gas. The simulation result shows that there is a papilionaceous distribution in combustion-gas flow around the double-faced deflector. Affected by the tip of the double-faced deflector, a cap shock wave generates in combustion-gas and a single-hump or dual-hump phenomenon observed there. Because of the compression of the deflecting face and the combustion-gas jet flow, there generate a secondary compressed shock waves and flow cell structure shaped like a fruit kernels. On going gas-jet test has validated certain deflecting features of the double-faced deflector on the basis of simulation.
出处
《导弹与航天运载技术》
北大核心
2006年第2期11-15,共5页
Missiles and Space Vehicles
