冲压增程弹丸进气道特性分析

Analysis on inlet performance of ramjet assisted range projectiles

关键词:  冲压发动机  弹丸  进气道  流场仿真

Key words:  Ramjet  Projectiles  Inlet  Flow field simulation

摘要:

采用块结构网格与二阶精度流场分区求解技术,对固体火箭冲压发动机增程弹丸超声速进气道特性进行了深入研究。通过数值模拟得到了对应于不同来流马赫数和攻角情况下,临界工况时,超声速进气道内外粘性流场复杂的波系结构,详细分析了来流马赫数和攻角对进气道性能的影响。结果显示,随着来流马赫数的增大,总压恢复系数显著降低,流量系数增大,同时随着来流攻角的增大,总压恢复系数及流量系数逐渐降低,而流场畸变指数则明显增大。

Abstract:

By means of block structure grid and second-order zonal solver method, the research on supersonic inlet performance of solid rocket ramjet assisted range projectiles was carried out. Complex wave structures of supersonic inlet at different inflow Mach number and attack angle related to critical status were achieved by numerical simulation. The influence of inflow Mach number and attack angle on the performance of inlet was analyzed. Results show that with the increasing of inflow Mach number, the total pressure recovery reduces rapidly. On the contrary mass flow ratio increases till to 1 at design Mach number. With the increasing of attack angle, the total pressure recovery and mass flow ratio reduces. However, flow distortion index increases obviously.