ME 440 Aerospace Engineering Fundamentals Numerical Assignment

QUESTION 1

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

QUESTION 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