Flow transients during rocket start-up and shut-down can lead to significant side loads on rocket nozzles. The capability to estimate these side loads computationally can streamline the nozzle design process. Towards this goal, the flow in a truncated ideal contour (TIC) nozzle has been simulated for a range of nozzle pressure ratios (NPRs) aimed to match a series of cold flow experiments performed at the NASA MSFC Nozzle Test Facility. These simulations were performed with varying turbulence model choices and with four different versions of the TIC nozzle model geometry, each of which was created with a different simplification to the test article geometry.
Simulation of Cold Flow in a Truncated Ideal Nozzle with Film Cooling
AIAA Propulsion and Energy Conference ; 2015 ; Orlando, FL, United States
2015-07-27
Conference paper
No indication
English
Simulation of Cold Flow in a Truncated Ideal Nozzle with Film Cooling (AIAA 2015-4152)
British Library Conference Proceedings | 2015
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