MAE 112 PROPULSION Winter 2008 Catalog Data:
Application of thermodynamics and fluid mechanics to basic flow processes and cycle performance in propulsion systems: gas turbines, ramjets, scramjets, and rockets. Prerequisite: MAE135. (Design units: 1
Due: February 16, 2007 MAE 112 Homework Assignment #4 1. Do Problem 18, Pages 214-5, Hill & Peterson. Note that specific thrust is defined as thrust per unit mass flow of air. It is used to normalize and to be able to compare engines of different siz
Due: February 22, 2008 MAE 112 Homework Assignment #5 1. Consider one-stage of a compressor with a 10% static pressure rise across the rotor followed by another 10% pressure rise across the stator (compounded to be 21%). The incoming flow has a veloc
MAE 112 Propulsion Homework Assignment #6 Due: February 29, 2008 Suppose we had two parallel flows with equal mass flow rates, one at a stagnation temperature of 1900R and the other at 2800R. Each flow had a stagnation pressure of ten atmospheres, a
MAE 112 Propulsion Homework Assignment #7 Due: March 7, 2008 1. Consider an ion rocket with a 1100 volt drop in potential between the accelerating electrodes placed 55 centimeters apart. Xenon of atomic weight 54 is the propellant. The charge to mass
MAE 112 PROPULSION FIRST MIDQUARTER EXAM February, 8, 2007
Do all three problems in ninety minutes. Books, notes and calculators can be used freely. I. (a) Establish the equations which can be employed for the calculation of the equilibrium composit
MAE 112 PROPULSION MIDQUARTER EXAM March 12, 2004
Do all three problems in one-hundred-and-ten minutes. Books, notes and calculators can be used.
1. Consider a turbine stage that has a polytropic efficiency of 0.98 for the stator (nozzle) and for th
MAE 112 PROPULSION SECOND MIDTERM EXAM March 13, 2007
Do all three problems in eighty-eight minutes. Books, notes and calculators can be used.
1. Consider a turbine stage that has a polytropic efficiency of 0.97 for the stator (nozzle) and for the r
MAE 112 PROPULSION MIDQUARTER EXAM February 13, 2004
Do all three problems in one-hundred-and-ten minutes. Books, notes and calculators can be used freely.
1. Consider a rocket nozzle with initial pressure and temperature of twenty-five atmospheres
1
Design Project Problem
1.1
Equation for TSFC,ST
In this design project, we define ST as:
ST =
T
T
(1 + f )ue + uef (1 + )u
=
=
m
a (1 + )
m
(1 + )
Correspondingly, the TSFC equation would be:
T SF C =
m
f
m
af
f
=
=
T
ST m
ST (1 + )
Remember to change
4. The ideal ramjet and turbojet thermal cycles are the ideal Brayton cycle as shown in
the figure below. Show that for constant Cp and the thermal efficiency of this cycle
is
1
th = 1
where
= p03 /pa
Thus, the thermal efficiency of an ideal ramjet or t
Due: February 1, 2008 MAE 112 Winter 2008 Homework Assignment #3 1. Consider a jet engine flying at a Mach number of 1.4. A normal shock sits at the entrance of the divergent diffuser. The diffuser entrance cross-sectional area is 2.5 ft2. The ambien
Due: January 25, 2008 MAE 112 Winter 2008 Homework Assignment #2 1. Consider a rocket engine that uses liquid oxygen and liquid ethanol (C2H5OH) fuel aka ethyl alcohol. The oxygen mass-flow rate is 2.00 times greater than the fuel massflow rate. Etha
MAE 112 PROPULSION FINAL EXAM March 25, 2004
Do all three problems in 120 minutes. Books, notes and calculators can be used freely.
1. Consider a combination of rocket propellants with a specific impulse (Isp) of 300 seconds for expansion from a pre
MAE 112 PROPULSION FINAL EXAM March 22, 2007 Do all four problems in 120 minutes. Books, notes and calculators can be used freely. 1. An afterburner has an exhaust temperature of 2700R into a nozzle and operates at five atmospheres of pressure. For e