Path: Propulsion/Rocket
% Computes the exhaust velocity of a O2/H2 rocket. -------------------------------------------------------------------------- Form: uE = UEO2H2( n, t0, p0, pE ) -------------------------------------------------------------------------- ------ Inputs ------ n (1,:) Number of molecules of H2 per O2 molecule t0 (1,1) Combustion temperature (deg-K) p0 (1,1) Combustion pressure (N/m^2) pE (1,1) Exhaust pressure (N/m^2) ------- Outputs ------- uE (1,:) Exhaust velocity --------------------------------------------------------------------------
Propulsion: Gas/Gamma Propulsion: Gas/MolWt Propulsion: Rocket/UE SC: Environs/MolWt2R Common: CommonData/SwooshWatermark Common: General/CellToMat Common: General/DeBlankLT Common: General/MatToCell Common: General/Watermark Common: Graphics/Mesh2 Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/PltStyle Common: Graphics/XLabelS Common: Graphics/YLabelS Common: Graphics/ZLabelS
Back to the Propulsion Module page