Path: Propulsion/Rocket
% Computes the ideal thrust coefficient for a nozzle with a diverging portion. If no outputs are specified it will generate a plot. If both e and p are vectors it will create a mesh plot. If only one is a vector it will create an xy plot. If only g is specified it will use e = linspace(15,600) and p = logspace(2,4). If no inputs are specified g will be set equal to 1.2. To get the real thrust coefficient multiply the result by an efficiency factor (typically 0.98). inf is a legitimate pressure ratio but you cannot generate plots with it. -------------------------------------------------------------------------- Form: [cF, x] = TCoeff( g, e, p ) -------------------------------------------------------------------------- ------ Inputs ------ g (1,1) Ratio of specific heats for the gas e (1,n) Area ratio (exit area/throat) p (1,m) Chamber pressure/ambient pressure ------- Outputs ------- cF (m,n) Thrust coefficient x (1,n) Ratio of exhaust pressure to chamber pressure --------------------------------------------------------------------------
Common: General/DeBlankLT Common: Graphics/Mesh2 Common: Graphics/NewFig Common: Graphics/PltStyle Common: Graphics/XLabelS Common: Graphics/YLabelS Common: Graphics/ZLabelS
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