Path: Propulsion/Rocket
% Computes the ideal exhaust velocity of a rocket. Since version 2. -------------------------------------------------------------------------- Form: uE = UE( gamma, m, t0, p0, pE ) -------------------------------------------------------------------------- ------ Inputs ------ gamma (1,n) Ratio of specific heats m (1,m) Molecular weight of the combustion products kg/mole 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 (m,n) Exhaust velocity --------------------------------------------------------------------------
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
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