(a) Calculate and carefully plot the specific thrust F/(gom), lbf/lbm/s, and specific fuel consumption S, lbm/h/lbf, vs design pressure ration for an ideal turbojet. The flight Mach number is to be 2.7, and you are given y = 1.4, To = 400R, h = 19,000 Btu/lbm, C = 0.24 Btu/lbm. R, TA= 6.8. Plot the results over the range from # = 1 to where the thrust goes to zero. (b) Obtain an analytic expression for the compressor ratio that just leads to zero thrust Tem in terms of y. Mo, and T. Check that the value calculated using the data of part (a) agrees with the graphical result of part (a). Plus f,nthno, andn. Plot S vs. F/m