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Unformatted text preview: ions used a rocket engine that produced a chamber pressure of about 710kPa, connected to a converging diverging exhaust nozzle (i.e. engine bell) with an throat area of 0.0366m2 and an exit area of 1.574m2. The gas flowing through the engine was a mixture of monomethyl hydrazine rocket fuel (40%) and oxidizers N204 (30%) and unsymmetrical dimethylhydrazine UDMH (30%). For the purposes of this question we will assume that this mixture behaves as an ideal gas with the properties of air, and that the temperature in the combustion chamber was 900K. (The titani...
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This document was uploaded on 02/20/2014.
- Spring '14