Path: Propulsion/Rocket
% Computes the exhaust velocity of a rocket from fuel lower heating value
The exhaust pressures are used as a ratio so can be any units.
Type UEQR for a demo.
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Form:
uE = UEQR( qR, gamma, p0, pE )
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Inputs
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qR (1,1) Heating value (J/kg)
gamma (1,1) Ratio of specific heats
p0 (1,1) Combustion pressure (N/m^2)
pE (1,:) Exhaust pressure (N/m^2)
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Outputs
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uE (1,:) Exhaust velocity (m/s)
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References: Martinez-Sanchez, M. "16.53 Course Notes"
M.I.T. 1979.
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Propulsion: Chemical/QRHydrogen Common: Atmosphere/StdAtm Common: Graphics/Plot2D
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