Interaction of external conditions with the internal flowfield in liquid rocket engines - A computational study

Computational studies have been conducted to examine the capability of a CFD code by simulating the steady state thrust chamber internal flow. The SSME served as the sample case, and significant parameter profiles are presented and discussed. Performance predictions from TDK, the recommended JANNAF reference computer program, are compared with those from PHOENICS to establish the credibility of its results. The investigation of an overexpanded nozzle flow is particularly addressed since it plays an important role in the area ratio selection of future rocket engines. Experience gained during this uncompleted flow separation study and future steps are outlined.