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homework4

# homework4 - MAE 113 Fundamentals of Propulsion Winter 2011...

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MAE 113 Fundamentals of Propulsion Homework Assignment 4 Winter, 2011 Due: Thursday, February 10 th in Class Page 1 of 2 Problem 1 Consider the flow through a rocket engine converging-diverging nozzle shown in figure 1. Assume that the gas flow through the nozzle is an isentropic expansion of a calorically perfect gas. In the combustion chamber, the gas which results from the combustion for the rocket fuel and oxidizer is at a pressure and temperature of 15 atm (abs) and 2500 K, respectively; the molecular weight and specific heat at constant pressure of the combustion gas are 12 g/mol and 4157 J/kg K, respectively. The gas expands to supersonic speed through the nozzle, with a temperature of 1350 K at the nozzle exit. (a) Assuming incompressible flow, calculate the pressure at the exit. (b) Assuming isentropic flow, calculate the Mach number and velocity at the exit. P 0 = 15 atm T 0 = 2500 K T e = 1350 K Figure 1: Diagram for problem 1 Problem 2 Air flows isentropically in a channel. At section (1) the Mach number is 0.3 and the area is 0.001 m

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homework4 - MAE 113 Fundamentals of Propulsion Winter 2011...

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