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.
Optimization of a Rocket Nozzle Side Load Reduction Device
Journal of propulsion and power ; 32 , 6
2016
Aufsatz (Zeitschrift)
Englisch
Optimization of a Rocket Nozzle Side Load Reduction Device
Online Contents | 2016
|Experimental Study on Rocket Nozzle Side Load Reduction
Online Contents | 2012
|Experimental Study on Rocket Nozzle Side Load Reduction
AIAA | 2011
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