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ME 440 Aerospace Engineering Fundamentals Assignment

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Added on: 2022-12-28 09:44:44
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Problem1.In the nozzle of a rocket engine the combustion gases enter a straight portion of diameter 2 m, are compressed to a diameter of 1 m, during which they are turned 45° (see the drawing below). For the conditions provided below, determine the exit velocity and the force the combustion gases apply on the nozzle wall. Nozzle Inlet Conditions: 455 kPa, 2500 K, 10 m/s Nozzle Exit Conditions: 65 kPa, 1434 K

Problem 2.The velocity for the wind tunnel in the ME 412 lab is determine from two pressure taps at the beginning and end of a smooth, converging section. For a pressure difference of 1.4 inches of water, determine the air velocity at the inlet to the converging section. Converging Section Inlet: 101 kPa, 298 K, 1 m x 1 m flow area Converging Section Outlet: 298 K, 1.8 m x 1.8 m flow area

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