Abstract: Fluidic thrust vectoring technology can provide good stealth performance and longitudinal maneuvering moment for supersonic tailless configurations, with advantages of fast response and light weight. The bypass shock vectoring nozzle does not need to draw air from the engine, which overcomes the problem of increasing the engine flow to increase the vector angle and reduces the burden on the engine. A study of the effect of bypass position on the performance of two-dimensional shock vectoring nozzle was conducted to lay the foundation for a better understanding of the performance of this nozzle and its practical applications. The results show that the throat bypass jet has the characteristics of both the shock vector and the throat skewing method, and that the inlet bypass jet performs better in the over-expanded condition, while the throat bypass jet has more advantages in the under-expanded condition. The separation mode after the jet significantly affects the nozzle vector performance. Closed separation makes the nozzle vector performance decrease significantly, and the nozzle pressure ratio related to the sudden change in vector performance of the throat bypass nozzle is smaller than that of the inlet bypass nozzle. In practice, it should be avoided to switch the separation mode from open separation to closed separation. Matching different bypass modes according to different expansion states can maximize the bypass shock vectoring nozzle performance.