类咽式进气道与典型侧压式进气道性能对比研究

Performance Comparison between Sim-jaws Inlet and Typical Sidewall Compression Inlet

针对火箭基组合循环发动机(Rocket Based Combined Cycle,RBCC)对进气道的大空域、宽速域、高性能设计需求,在相同约束条件下设计了矩形截面类咽式进气道和典型侧压式进气道,采用数值仿真的方法对两种进气道的流动特征、速度特性、攻角特性和阻力特性进行了对比研究。结果表明两种进气道内均存在扫掠激波-边界层相互干扰,类咽式进气道流场特征呈现出左右结构而侧压式进气道为上下结构;在不同来流条件下,类咽式进气道在流量捕获能力和降低溢流阻力上均有明显优势。可为宽范围高性能进气道的设计提供一定参考。

In response to the large airspace,wide speed range,and high-performance design requirements of the RBCC engine inlet,a rectangular Sim-jaws inlet and a typical sidewall compression inlet are designed under the same constraints.The characteristics of flow,velocity,angle of attack and drag of the two inlets are compared by numerical simulation.The results show that there are sweeping shock waves/boundary layers interactions in both inlets,and the flow field of the Sim-jaws inlet presents a left-right structure while the sidewall compression inlet has an upper-lower structure.The Sim-jaws inlet has significant advantages in flow capture ability and reducing overflow drag under different inflow conditions.Some references are provided for the design of wide range and high-performance inlet.