Path: Propulsion/Chemical
% H2/O2 rocket model.
Type RocketH2O2 for a demo of the Space Shuttle Main Engine at sea level.
If p0 is any character it will return a default data structure.
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Form:
[thrust, uE, qR] = RocketH2O2( p0, pA, aStar, aE, f, tP )
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Inputs
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p0 (1,1) Chamber pressure (N/m^2)
pA (1,1) Ambient pressure (N/m^2)
aStar (1,1) Throat area (m^2)
aE (1,1) Exit area (m^2)
f (1,1) Mixture ratio (kg O2/kg H2)
tP (1,1) Preheat temperature (deg-K)
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Outputs
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thrust (1,1) Thrust (N)
uE (1,1) Exhaust velocity (m/s)
qR (1,1) Energy per unit mass (J/kg)
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References: http://en.wikipedia.org/wiki/Space_Shuttle_Main_Engine
Hill, P. and C. Peterson, "Mechanics and Thermodynamics
of Propulsion", p. 353-361.
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