冲压增程弹丸进气道复杂湍流流场数值仿真

Numerical Simulation on the Inlet Complex Turbulent Flow ofRamjet Assisted Range Projectiles

应用二阶隐式TVD格式对固体火箭冲压发动机增程弹丸超音速进气道内部湍流流场进行了数值仿真。通过对交叉楔面超音速湍流流场数值仿真结果分析,并与实验结果比较,显示该算法和编制的程序是可靠的,能够准确仿真具有激波—激波、激波—边界层相互作用的复杂湍流流场。通过数值仿真得到了不同出口反压条件下超音速进气道湍流流场复杂的波系结构,并分析了流场的发展过程和出口反压对进气道性能的影响,为今后进一步深入研究提供了理论基础。

The numerical simulation of supersonic inlet internal turbulent flow of solid rocket ramjet assisted range projectiles was performed by 2-order implicit TVD. Through an analysis on the numerical simulation results of intersecting wedges supersonic turbulent flow and the comparison between numerical results and experimental data, the results show that the algorithm used in this paper and the code formed from it are credible. Above-mentioned algorithm and code can predict complex turbulent flow of shock/shock and shock/boundary layer interaction exactly. Lastly, complex wave structures of supersonic inlet under different outflow pressures were presented by numerical simulation. The flow field development progress and the influence of outflow pressure on the working performance of inlet were also analyzed. The theoretical method for later study is provided in the paper.