ME 10.412 / ME 10.512 Rocket Propulsion Week 6 Thermochemical Rocket Calculations Class Notes - Page: 1 Text: Sutton Ch. 5 Homework Assignment 1. NASA 1 kW Arcjet. For a NASA 1 kW arcjet operating on hydrazine (N2H4), calculate the performance as a function of average chamber temperature, Tc. Specifically, given the following parameters: Pc = 50 psia Pa = 0.2 Torr Ae/At = 150 dt = 0.64 mm Generate the following plots using the NASA CEA Code: a. Plot all equilibrium species mole fractions as a function of chamber temperature (1000 < T c < 10,000 K) b. Plot C* vs. chamber temperature (1000 < T c < 10,000 K) c. Plot vs. chamber temperature (1000 < T c < 10,000 K) d. Plot Average MW vs. chamber temperature (1000 < T c < 10,000 K) 2. Hybrid Rocket Motor Design Project. Using the NASA CEA Code, generate the following plots for an HTPB/GOX hybrid rocket motor: a. Tc as a function of O/F ratio. b. as a function of O/F ratio. c. Average MW of chamber products vs. O/F ratio. d. C* vs. O/F ratio e. All equilibrium species mole fractions vs. O/F ratio. Assume Pc = 150 psia. Also, note that HTPB is not in the NASA database. To use it as a fuel, you have to input the heat of formation and chemical formula in the reactant section of the .inp file as follows: name HTPB C 7.337 H 10.982 O .058 wt%=100 h,cal=-2970.00 t(k)=298.15 GOX solid fuel