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MAE 1202 Lab Hmk 3

# MAE 1202 Lab Hmk 3 - MAE 1202 Aerospace Practicum...

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MAE 1202: Aerospace Practicum Laboratory Homework #3 Due: February 10, 2012 YOU: Another laboratory homework assignment?!? But this is only a 2 credit class and there are already a bunch of lecture homework problems due next Wednesday. ME: This laboratory exercise is designed to help you with the lecture-based homework and even give you some of the answers to the lecture homework problems. It is also designed to give you more practice using MATLAB and to show you how when used by the forces of good it can be an extremely powerful engineering tool. 1. Consider homework problem 4.8: A supersonic nozzle is also a convergent-divergent duct, which is fed by a large reservoir at the inlet to the nozzle. In the reservoir of the nozzle, the pressure and temperature are 10 atm and 300 K, respectively. At the nozzle exit, the pressure is 1 atm. Calculate the temperature and density of the flow at the exit. Assume the flow is isentropic and, of course, compressible. The following MATLAB script will give you the answer to this problem. As you type in this script, make sure that you completely understand each line of the code . All the equations are taken from Equation 4.37 in the textbook. % Script to calculate isentropic relations % based on Equation 4.37 from Introduction to Flight close all; % closes any plot windows that may be open clear all; % clears all variables from memory from any previous scripts gamma=1.4; % Specific heat ratio for air R_universal=8314; % Universal gas constant M=28.97; % Molecular weight of air R=R_universal/M; % Gas constant for air % Enter relevant values p_inlet_atm=10; % inlet pressure in atmospheres p_inlet_pa=p_inlet_atm*101325; % inlet pressure in Pascals or N/m^2 p_exit_atm=1; % exit pressure in atmospheres p_exit_pa=p_exit_atm*101325; % exit pressure in Pascals or N/m^2 T_inlet=300; % inlet pressure in Kelvin

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MAE 1202 Lab Hmk 3 - MAE 1202 Aerospace Practicum...

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