USE NASA CEA ( CHEMICAL EQUILIBRIUM ANALYSIS ) TO DETERMINE PLOTS !!!

Question 1 Plot (i) Adiabatic Flame Temperature (Tflame) versus Oxidizer to Fuel (0/F) ratio and (ii) characteristic velocity (c*) versus Oxidizer to Fuel ratio graphs of propellant combinations stated below. Use NASA CEA (chemical equilibrium analysis) to determine plots. Change your O/F between 1 and 10 with the 0.5 step size. Plot values in the same graph. a. C32H66/GOX b. C32H66/N20 C. C32H66/Al/N20 (with 20% aluminum by mass in the fuel mixture) d. C32H66/Al/N20 (with 40% aluminum by mass in the fuel mixture) e. Compare Tflame and c* values of propellant combinations. Which propellant combination provides better performance? f. Calculate thrust (T), specific impulse (Isp), total impulse (Itot) and average thrust () values of propellants plot 0/F versus Isp. Assume you have total mass flow rate (Mtot) of 250 grams/seconds with 10 seconds of burn time (tv), nc = 0.95, n = 0.97,90 = 9.81 m/s2. You should find heat of formation values of N, 0 and C32H66 (paraffin wax) from the literature