攻角对炮射冲压发动机进气性能的影响

The Influence of Attack Angle on the Inlet of the Ramjet Engine

采用结构化网格与二阶精度流场分区求解技术,对某冲压发动机超音速进气道特性进行了深入研究。通过数值模拟得到了在飞行高度3000m、飞行速度2.5Ma、不同攻角情况下,超音速进气道内外粘性流场复杂的波系结构,详细分析了攻角对进气道总压、流量等工作参数的影响。结果显示,随着来流攻角的增大,此进气道总压恢复系数变化不大,流量系数逐渐降低,而流场畸变则明显增大。

By means of block structure grid and second-order zonal solver method, the research on supersonic inlet performance of ramjet was carried out. Complex wave structure of supersonic inlet at 3000m, 2.5Ma and different attack angle related to critical status were achieved by numerical simulation. The influence of attack angle on total pressure, mass flow ratio of inlet was analyzed. Results show that the increasing of attack angle, the total pressure recovery chan- ges a little and mass flow ratio reduces. However,flow distortionindex increasers obviously.