One of the major tasks for the development of novel airbreathing space transportation systems, operating from usual airports by horizontal take off and landing, is the integration of an advanced propulsion system in the cell of that spacecraft. The air intake and in particular the free expansion nozzle affect not only the efficiency of the engine but also the forces and moments, and with that, the control of the complete spacecraft. Therefore, it is necessary to know in detail the flow fields through such nozzles and its interaction with the external airflow. Another project deals with conventional rocket motor nozzles whereby injection of turbine exhaust gases in the expansion part of the nozzle the wall of the nozzle is cooled (filmcooling concept) and the thrust is slightly increased. Theoretical investigation of these and other nozzles is the objective of this paper. Euler and boundary layer methods will be applied to predict the flow fields of the nozzles where special emphasis is laid on the consideration of real gas effects. The theory of the Euler method will be described in detail while for the second order boundary layer method the governing equations are presented and the range of its applicability is shortly discussed. Finally results for a variety of nozzles will be given.
Aerothermodynamics of Nozzle Flows for Advanced Hypersonic Propulsion Systems
1992
11 pages
Report
No indication
English
Jet & Gas Turbine Engines , Spacecraft Trajectories & Flight Mechanics , Aerodynamics , Aerothermodynamics , Air breathing engines , Gas turbines , Hypersonic flight , Nozzle flow , Nozzle walls , Propulsion system configurations , Air intakes , Exhaust gases , Propulsion system performance , Real gases , Rocket engines , Foreign technology
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