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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 (1,:) Fuel name ------- Outputs ------- uE (1,:) Exhaust velocity (m/sec) --------------------------------------------------------------------------
Common: Graphics/Plot2D Propulsion: Chemical/Fuels Propulsion: Rocket/UE
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