Numerical Tool Optimization for Advanced Rocket Nozzle Performance Prediction

A number of Altitude-Compensating Nozzle concepts have been developed through the years, to reduce nozzle performance losses. One of the most promising concepts is the dual- bell nozzle, where the flow is capable of auto-adapting at low and high altitude without the use of mechanical devices. This paper focuses on the optimization and validation of an in- house solver for the prediction of the flow field in advanced rocket nozzles, with emphasis on dual-bell rocket nozzles. Numerical efforts are concentrated on predicting transition from one operating mode to the other, since low and high altitude operating modes are both well known stable conditions. Both steady state and transient problems are considered and the performances of different numerical schemes are investigated.