Path: Propulsion/Rocket
% Computes throat area (A*) for a given thrust -------------------------------------------------------------------------- Form: aStar = ThrustToAStar( fuel, thrust, p0, pA, e ) -------------------------------------------------------------------------- ------ Inputs ------ fuel (1,:) Fuel type, ex. 'air','nitrogen' thrust (1,1) Thrust level (N) p0 (1,1) Chamber pressure (N/m^2) pA (1,1) Ambient pressure (N/m^2) e (1,1) Area ratio (exit area/throat area) ------- Outputs ------- aStar (1,1) Throat area (m^2) -------------------------------------------------------------------------- See also GasProperties, TCoeff --------------------------------------------------------------------------
Propulsion: Rocket/TCoeff Common: General/DeBlankLT Common: General/StrMtch Common: Graphics/Mesh2 Common: Graphics/NewFig Common: Graphics/PltStyle Common: Graphics/XLabelS Common: Graphics/YLabelS Common: Graphics/ZLabelS Common: Materials/GasProperties
Back to the Propulsion Module page