NASA has designed a standard rocket engine to use on their new Mars lunar rover. The engine burns with a stoichiometric mixture of liquid hydrogen and oxygen. The reaction chamber for combustion is a cylinder with a length of 750 mm and a diameter of 600 mm (see diagram below). Combustion produces 108 kg/s of exhaust gas. Assuming combustion is complete (i.e. no side reactions), calculate the rate of reaction of H₂ and O₂ in mol L¹ s¹. H₂ 0₂ 600 mm 750 mm Exhaust Gas 108 kg/s

Pure oxygen (O2) at high pressure is sometimes used in chemical processes instead of air to avoid the high cost of pressurizing all the N2 that inevitably comes with use of air as well as additional cost of capital equipment such as heat exchangers, reactors, etc. through which the (generally unnecessary) nitrogen flows. The decision of which to use (pure O2 or air) is based on the tradeoff between the cost of obtaining the pure O2 (via cryogenic distillation or membrane separation) versus the cost of all the unnecessary N2 running through the process. Your process utilizes O2 at -70°C and 10.2 atm absolute. If the mass flow rate of O2 is 8.0 kg/min, determine the volumetric flow rate of the O2 stream using (a) the ideal gas EOS and (b) the SRK EOS.

Calculate the freezing point of a 2.0m solution of NaCl in water? Remember that NaCl is an electrolyte. The normal freezing point of pure water is 0.00°C. Kf(water) =1.86°C/m

Nitrogen gas enters a 0.450 m diameter pipe at 30.0 °C, 2.60 atm (absolute), and 6.30 m/s. The pipe rises 24.0 ft and then falls 99.0 ft. The nitrogen gas exits the pipe at 30.0 °C and 1.10 atm (absolute). The ultimate goal is to find AEK and AEp in the process. Assume N₂ behaves ideally. What is V₁, the volumetric flow rate of nitrogen gas into the pipe section? V₁ = 1 What is m, the mass flow rate into the pipe? z, ft T, °C P, atm (absolute) u, m/s z, ft T₂ °C P, atm (absolute) u, m/s m³/s