Performance of a Monomethylhydrazine-Dinitrogen Tetroxide Rocket - Maple Application Center
Application Center Applications Performance of a Monomethylhydrazine-Dinitrogen Tetroxide Rocket

Performance of a Monomethylhydrazine-Dinitrogen Tetroxide Rocket

Author
: Maplesoft AuthorSamir Khan
Engineering software solutions from Maplesoft
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Liquid monomethylhydrazine (CH6N2) and dinitrogen tetroxide (N2O4) are burned in the combustion chamber of a rocket engine. The oxidizer to fuel ratio is 2.5 (i.e. in the ratio of 1 mole of CH6N2 to 1.2518 moles of N2O4).

This application will calculate
  • the adiabatic flame temperature and composition of the combustion products (i.e. in the combustion chamber)
  • the pressures and temperatures in the throat and exit
  • and the theoretical rocket performance, including the ideal specific impulse, characteristic velocity, and sonic velocity.

Application Details

Publish Date: March 09, 2018
Created In: Maple 2018
Language: English

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