Optimization of a Rocket Nozzle Side Load Reduction Device

摘要

During transient start-up and shutdown of rocket engines under sea-level conditions, the flow inside the supersonic part of the nozzle separates from the wall. The separated flow is asymmetrically distributed around the circumference and hence induces side loads. A cold flow subscale test campaign was carried out at DLR to study a device that reduces the side loads of a thrust-optimized parabolic nozzle under transient conditions. A detailed parametrical study was performed. The experimental data demonstrated and quantified the side load reduction potential of the device.