Path: Propulsion/Rocket
% Computes the thrust and exhaust velocity for an ideal rocket. p0 or e may be vectors. If p0 or e is an array then the other will be turned into an array of equal length. Type IdealRkt for a demo. -------------------------------------------------------------------------- Form: [thrust, uE, iSP, cT, pRatio] = IdealRkt( g, aStar, p0, pA, t0, e, m ) -------------------------------------------------------------------------- ------ Inputs ------ g (1,1) Ratio of specific heats aStar (1,1) Throat area (m^2) p0 (n) Chamber pressure after heating (N/m^2) pA (1,1) Ambient pressure (N/m^2) t0 (1,1) Temperature after heating (deg-K) e (m) Area ratio (exit area/throat area) m (1,1) Molecular weight (kg/mole) ------- Outputs ------- thrust (n,m) Thrust level (N) uE (n) Exhaust velocity (m/sec) iSP (n) Specific impulse (sec) cT (m) Thrust coefficient pRatio (m) Pressure ratio --------------------------------------------------------------------------
Propulsion: Rocket/TCoeff Propulsion: Rocket/V2Isp SC: Environs/MolWt2R Common: Graphics/Mesh2 Common: Graphics/Plot2D
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