In a rocket engine running with {H2+0.3O2}, for the same engine pressure and mass flow, the adapted raw thrust:Group of answer choicesWill be lower changing to a rich hydrocarbon/oxygen mixtureWill be higher changing to rich hydrocarbon/oxygen mixtureIs not affected by the choice of mixtureRequires a fuel air ratio of 2

For an adapted rocket engine with fixed geometry, thrust, chamber pressure, increasing the mixture ratio past the stochiometric point towards richer mixture:Group of answer choicesIncreases the mass flow requiredRequires zero mass flowReduces the mass flow requiredDoes not affect the mass flow requirements

Which ONE of the following does NOT change the flux of metabolites through the various pathways?Group of answer choicesAn increase of intermediate metabolites.A decrease in oxygen.The phosphorylation and regulation enzyme.The standard free energy change.

A gaseous air‑fuel mixture in a sealed car engine cylinder has an initial volume of 600.mL at 1.0atm. To prepare for ignition of the fuel, a piston moves within the cylinder, reducing the volume of the air‑fuel mixture to 50.mL at constant temperature. Assuming ideal behavior, what is the new pressure of the air‑fuel mixture?

Air enters a jet engine through section 1 with an area of A1=0.5 m2 at a (relative) speedof 250 m/s. The pressure at the entrance is atmospheric pressure (approximately 105 Pa)and the temperature is 300 K. Inside the engine, the injected fuel mixes perfectly withair, with fuel to air mass ratio of 1:30. The enthalpy and the kinetic energy flow rate ofthe fuel can be neglected at the fuel inlet. The combustion releases a heat per unit mass(of air) of 200 kJ/kg, after which the mixture is expanded through a nozzle to the exitsection 2 whose area is A2= 0.4 m2. The product of combustion can be taken to havethe same properties of air (such as Cp=1.005 kJ/kg k, γ=1.4 and so on). The nozzleperfectly expands the flow such that at the exit 2, the pressure is atmospheric pressure.The temperature of the flow at the exit is 400 K. The figure below shows a roughschematic of the engine and the flow. Find the thrust generated by the engine.

Air enters a jet engine through section 1 with an area of A1=0.5 m2 at a (relative) speedof 250 m/s. The pressure at the entrance is atmospheric pressure (approximately 105 Pa)and the temperature is 300 K. Inside the engine, the injected fuel mixes perfectly withair, with fuel to air mass ratio of 1:30. The enthalpy and the kinetic energy flow rate ofthe fuel can be neglected at the fuel inlet. The combustion releases a heat per unit mass(of air) of 200 kJ/kg, after which the mixture is expanded through a nozzle to the exitsection 2 whose area is A2= 0.4 m2. The product of combustion can be taken to havethe same properties of air (such as Cp=1.005 kJ/kg k, γ=1.4 and so on). The nozzleperfectly expands the flow such that at the exit 2, the pressure is atmospheric pressure.The temperature of the flow at the exit is 400 K. The figure below shows a roughschematic of the engine and the flow. Find the thrust generated by the engine