The jet engine on a test stand, shown in the figure, admits air at 20oC and 1 atm at section 1, where the area is 0.5 m2 and the velocity is 250 m/s. The fuel-to-air ratio is 1:30. The air leaves at section 2 at atmospheric pressure and a higher temperature. The exit velocity is 900 m/s and the area is 0.4 m2 . Compute the horizontal test stand reaction Rx needed to hold the engine fixed.

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Problem-5: In a CD nozzle with a throat area of 0.75 m² of a rocket engine, gas at 7.5 MPa and temperature of 3200 K is in combustion chamber, is expanded fully to (nozzle exit pressure) 10.5 kPa for producing thrust. Assuming flow to be frozen and isentropic, Also, Assume, gamma, y 1.2 and molecular weight, MW = 24 kg/kmol, Assume, universal gas = constant = 8314 J/Kg K mol Determine: (1) the exit Mach number, (2) the maximum exit mass flow rate passing through this nozzle, and (3) the exit area (4) If ambient pressure, i.e. pressure outside nozzle = 10.5 kPa, What is the thrust developed? Fuel Oxidant Combustion zone Mixture of Hot gas at high pressure and Temprature Expansion Through Nozzle High velocity exhaust Liquid Propellant Rocket

The initial condition of air in an air compressor is 98kpa and 27C and discharges at 500kpa. The bore and stroke are 360mm and 390mm, respectively with percent clearance of 7% running at 350rpm. Find the mass flow of air in kg/s at suction. Ans: 0.22