Path: Propulsion/Nuclear
% Compute the exhaust velocity for a nuclear rocket with H2 fuel. -------------------------------------------------------------------------- Form: uE = NuclearThermalUE( t, fuel ) -------------------------------------------------------------------------- ------ Inputs ------ t (1,:) Temperature (deg-K) fuel '' Fuel name, default 'Hydrogren' ------- Outputs ------- uE (1,:) Exhaust velocity (m/sec) -------------------------------------------------------------------------- See also: Fuels --------------------------------------------------------------------------
Propulsion: Chemical/Fuels Propulsion: Rocket/UE Common: Graphics/Plot2D
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