Abstract:
Supersonic flow structure with lateral jet is highly complex, since it contains bow shock, separation shock, vortex, and other complicated physical phenomena. The present investigation was conducted on lateral jet interaction over supersonic missile crossflow by solving the Navier-Stokes equations with the software MFlow developed by China Aerodynamics Research and Development Center (CARDC). The momentum ratio principle was discussed by comparing a gaseous injection in supersonic flow with an air injection, The comparison indicates that the momentum ratio principle is reliable in the present simulation. Besides, numerical simulation was applied to a missile configuration with multiple spouts. The flow structure around the missile and the amplification factor were analyzed, and the influence pattern was obtained for different spout arrangements. This investigation is useful in providing basic understanding on designing missile with revision control system (RCS).