Consider an ideal turbojet with an afterburner at flight conditions: To = 220 K, P= 20 kPa, and M. = 0.8. Calculate and plot: 1) the specific thrust (T / mdot) versus the afterburner stagnation temperature (T+7) 2) Isp (specific impulse) versus the afterburner stagnation temperature (Tt7) Use the following parameters for your calculations: T3 = 20, T4 = = 1600 K, and I g = 1600 to 2500 K.
The fuel heat of combustion is hf = 42,800 kJ/kg and the properties of air are: y = 1.4, R = 287J/kg-K, and Cp = 1005 J/kg-K.

Agas contained within a piston-cylinder assembly e end nation about same energy states, 1 and 2, where pi 10 bar, v undergoes two processes, a and b, between the sam 0.1 m3, ui-400 kj and p2 1 bar, v2 1.0 m2, u2 200 kj: process a: process from 1 to 2 during which the pressure- volume relation is pv constant process b: constant-volume process from state 1 to a pressure of 2 bar, followed by a linear pressure-volume process to +20 0 state 2 kinetic and potential energy effects can be ignored. for each of the processes a and b, (a) sketch the process on p-v coordinates, (b) evaluate the work, in kj, and (c) evaluate process the heat transfer, in kj