The effects of rocket engine size on the effective exhaust velocity, for geometrically similar nozzles, are investigated as far as wall friction and finite-rate chemistry are concerned. Propulsion systems burning LH/LOX, LCH4/LOX and kerosene/LOX combinations are considered. The engine performance is estimated via CFD codes based on a particularly convenient formulation. It is found that both friction and finite-rate chemistry lead to performance steadily increasing with engine size, and the two effects are quantified individually. This has implications on the choice of the optimal number of engines per stage, and possibly the number of thrust chambers per engine.
Size Effects on the Performance of Liquid Rocket Engines Fed with LH/LOX, LCH4/LOX and Kerosene/LOX / Lentini, Diego; Nasuti, Francesco; Onofri, Marcello. - (2003). (Intervento presentato al convegno 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference tenutosi a Huntsville; United States nel 20-23 luglio2003).
Size Effects on the Performance of Liquid Rocket Engines Fed with LH/LOX, LCH4/LOX and Kerosene/LOX
LENTINI, Diego;NASUTI, Francesco;ONOFRI, Marcello
2003
Abstract
The effects of rocket engine size on the effective exhaust velocity, for geometrically similar nozzles, are investigated as far as wall friction and finite-rate chemistry are concerned. Propulsion systems burning LH/LOX, LCH4/LOX and kerosene/LOX combinations are considered. The engine performance is estimated via CFD codes based on a particularly convenient formulation. It is found that both friction and finite-rate chemistry lead to performance steadily increasing with engine size, and the two effects are quantified individually. This has implications on the choice of the optimal number of engines per stage, and possibly the number of thrust chambers per engine.I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.