Exhaust Shock Patterns Inside Over-Expanded Rocket Nozzles

Kurzfassung

An experimental study has been carried out to investigate the exhaust flow patterns from two types of rocket nozzles, each with a different expansion angle downstream of the last point of arc forming the throat. It is observed that this higher expansion angle results in the formation of an internal shock that influences the shock structure development considerably and also influences the side-load behavior in these nozzles significantly.