作　　者： ; ; ;

机构地区： 中国科学院广州能源研究所

出　　处： 《微纳电子技术》 2010年第3期163-169,共7页

摘　　要： 以FLUENT6.1为工具,利用数值计算求解二维稳态可压缩N-S方程和欧拉方程,模拟了扩张比为5.4的收缩-扩张微喷管内超音速流体流动,分析了黏性耗散对微喷管内部流体流速分布和静压力分布的影响,进而研究了黏性耗散对微喷管的流量系数和推力效率等推进性能参数的影响。数值计算结果表明,在微喷管收缩段,惯性力影响相对较大,黏性耗散对流体流动的影响相对较小;在微喷管扩张段,黏性耗散的影响相对增加,惯性力影响相对减小,黏性耗散将影响微喷管内流体的流动方向;在喷管出口,主流流体偏离的程度减小,进而影响微喷管的推进性能参数。 Based on the FLUENT6.1 software, the supersonic flow in micro convergent-divergent nozzle was simulated through solving the two-dimensional steady compressible Navier-Stokes equations and Euler equations with the numerical calculation, where the expansion ratio of the nozzle was 5.4. The effects of vicious dissipation on velocity contours and static pressure contours in the micro nozzle were analyzed. Besides that, the influences of vicious dissipation on flow coefficient and thrust efficiency were further studied. Numerical computing results show that the impact of inertia force is greater and the effect of viscous dissipation on the fluid flow is relatively less in the micro nozzle convergent section. In the micro nozzle divergent section, the impact of inertia force becomes less, while the influence of viscous dissipa-tion grows greater, and the fluid flow direction is affected. At the exit of the nozzle, the deviation of the mainstream fluid becomes less, and affects the thrust performance of the micro nozzle.

关 键 词： 数值计算 黏性耗散 微喷管 流量系数 推力效率

领　　域： [电子电信] [航空宇航科学与技术] [航空宇航科学技术]