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Theoretical Performance of a LOX-LH2 Rocket - Maple Application Center
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Applications
Theoretical Performance of a LOX-LH2 Rocket
Theoretical Performance of a LOX-LH2 Rocket
Author
:
Samir Khan
0
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Liquid hydrogen (at 20.27 K) and liquid oxygen (at 90.17 K) are burned in the combustion chamber (with an infinite area ratio) of a rocket.
The combustion products contain H
2
, O
2
, H, O, OH, HO
2
and H
2
O
2
This application will calculate
the adiabatic flame temperature and composition of combustion products
the pressures and temperatures in the throat and exit
and the theoretical rocket performance, including the ideal specific impulse, characteristic velocity, sonic velocity and more
Assumptions:
The combustion chamber is large compared to the throat, hence the assumption of an infinite area ratio
The flow composition does not change through the nozzle expansion (i.e. reaction rate is slow compared to flowrate). This is also known as "frozen" flow
Application Details
Publish Date
:
March 09, 2018
Created In
:
Maple 2018
Language
:
English
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thermodynamics
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