Experimental research on vector control features of a pulse detonation tube with fluidic nozzle

Fluidic nozzle is attractive on adjusting the effective area ratio according to the fluctuated exhaust gas in a pulse detonation engine, which can help to reduce over-expansion and under-expansion losses and improve the propulsion performance. The present paper seeks to explore the operation characteristics and thrust vector features of a two-dimensional and visualized fluidic nozzle attached to a single-cycle detonation tube, spike pressures, velocities of the detonation waves, and flow field structures in the nozzle were captured. The results demonstrated that the front shock wave was remarkably weakened with a decrease up to −57% when throat injection was utilized, and the exhaust process was extended up to 17.7%. Meanwhile, the divergent injections were proved to be effective on weakening the reflected shock waves in the nozzle, preventing the formation of Mach disk, and adjusting the effective boundary of divergent section from conical into bell-shape. In addition, the asymmetric injections were validated to be effectual on adjusting the direction of the exhaust gas. Reflected shock waves were weaker in the divergent injection side, and the exhausted gas was deviated from the injection side obviously.