For a turbofan engine operating at $M_o = 0.75$ at $H = 40$ kft, $\dot{m}_o = 2405 \frac{lbm}{s}$, $h_{PR} = 18 \, 400$ BTU/lbm, $\pi_c = 10$, $\pi_f = 1.75$, and $\alpha = 6.5$, plot the specific thrust, TSFC, thermal and propulsion efficiencies as a function of the turbine inlet temperature from $T_4 = 2250$ to $4000^\circ$R.