A new method to determine the throat conditions for chemical reacting flows, such as occur in rocket nozzles (frozen and equilibrium) is presented. Contrary to other methods, the throat region is defined by an analytical criterium which can be solved directly, and not in an iterative way. An outline is given of the computational method, while results are presented in a graphical form. The method proves to be well applicable to digital computers.
The Determination of the Throat Conditions for Equilibrium and Frozen Flows in Rocket Motor Nozzles
1976
44 pages
Report
No indication
English
ROCKET NOZZLE MODELLING - Throat Flow Modelling of Expansion Deflection Nozzles
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