Methods are presented for calculating net thrust using air specific-impulse data for various fuels. Nomographic solutions are given to adapt the methods to turbojet-afterburner calculations. These nomographs can be used to compute net thrusts obtained by expanding exhaust gases to either a Mach number of 1.0 or the ambient static pressure at the nozzle exit. Thermodynamic data for several fuels are also presented.
展开▼
