Experimental study on rocket nozzle side load reduction

Kurzfassung

The flow during transient start-up and shut down in all rocket engines operated on sea level under ambient conditions will separate inside the supersonic part of the nozzle. A separated nozzle flow is circumferential asymmetric distributed and induces therefore high side loads. DLR Lampoldshausen carried out a cold flow subscale test campaign to study devices that can reduce the side loads during transient engine operation. These devices can be installed either on ground test facilities or launch pads. A detailed parametrical study was performed and experimental data demonstrate the potential of the device to reduce side loads.