Performance Analysis of Micro Thrust Vector Control for Supersonic Micronozzles With Different Divergent Sections

In this study, supersonic micronozzles with secondary flow injection were examined experimentally and numerically for thrust vector control applications. Two divergent sections designs of bell-type and conical-type were investigated with secondary flow pressure varying from 50, 60, 80, and 100 kPa. The pressure rise introduced by the secondary flow injection can be clearly observed from both experimental and numerical data. The conical-type divergent section can provide better performance with an exit flow turning angle up to 2.68 degrees. However, the exit flow turning angle decreases with the increase of secondary flow pressure due to the shock wave moving inside the nozzle.