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
MAE112 Homework 6 solution
March 15, 2017
1
Problem 7-1
1.1
part a
Figure 1: part a
Case 1 is a compressor because c has same direction as U . w2 < w1 and C3 < C2 indicates that pressure
rise in rotor and stator.
Case 2 is a turbine because c has opposi
MAE 112 Homework #5
Feb. 9, 2017
Due 11:00pm Fri. Feb. 17, 2017
Reading: Chapter 5: 5.1-5.5
1. For the ideal ramjet engine, do the following.
(a) Show that the specific thrust is
#
"
1/2
p
p
1 2
T
1
= M RTa (1 + f ) T04 /Ta 1 +
M
ST =
m
a
2
(b) Assuming f
MAE 112 Homework #3
Posted on January 29, 2017
Due 11:00pm, Fri. Feb. 3, 2017
Required Reading:
Distributed Lecture Notes on 1D Channel Flow;
Chapter 2: Sections 2.1-2.3, and Chapter 3; Chapter 5, Sections 5.1-5.5
1. A hypersonic vehicle is to fly at a Ma
MAE 112 Homework #6
Posted Feb 18, 2017
Due 11:00pm Fri. Mar. 3, 2017
Reading: Chapter 5: 5.1-5.5
1. Compare the takeoff thrusts of two engines operating with the same core engine airflow
rate, compressor exit pressure (12 atm), and turbine inlet temperat
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
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
MAE 112 Homework #2
Jan. 20, 2017
Due 11:00pm Friday, Feb. 27, 2017
Reading Assignment:
Chapter 2: 2.1-2.3; Chapter 4: 3.1-3.4, 3.7; Chapter 5: 5.1-5.3
1. Consider the acceleration of a streamtube through a conventional unshrouded aircraft
propeller from
MAE 112 Homework #1
Posted on January 13, 2017
Due to Canvas at 11:00pm Fri. January 20, 2017
Reading: Chapter 1, Chapter 2: 2.1-2.3, Chapter 5: 5.1-5.2
1. On a frictionless level surface lie two spheres with mass m and mp neighboring to
each other. Suppo
MAE 112 Homework #7
Posted Mar. 2, 2017
Due 11:00pm Fri. Mar. 10, 2017
Reading: Chapter 7: 7.1-7.5, 7.7-7.8, 8.1-8.3
1. Problem 7.1
2. Problem 7.2
3. Problem 7.3
4. Problem 7.5
5. Problem 7.9
6. Problem 7.11
See the attached pages.
1
MAE 112 Homework #3 with Solutions
Posted on January 29, 2017
Due 11:00pm, Fri. Feb. 3, 2017
Required Reading:
Distributed Lecture Notes on 1D Channel Flow;
Chapter 2: Sections 2.1-2.3, and Chapter 3; Chapter 5, Sections 5.1-5.5
1. A hypersonic vehicle is
MAE 112 Homework #5
Feb. 9, 2017
Due 11:00pm Fri. Feb. 17, 2017
Reading: Chapter 5: 5.1-5.5
1. For the ideal ramjet engine, do the following.
(a) Show that the specific thrust is
#
"
1/2
p
p
T
1 2
1
ST =
= M RTa (1 + f ) T04 /Ta 1 +
M
m
a
2
(b) Assuming f
MAE 112 Final Exam Mar. 18, 2016
1:30-3:30pm, closed-book, 6 letter-size, double-sided sheets of notes allowed.
No electronic devices of any kind is allowed.
Total 40 points.
Name:
Student ID:
Problem 1: Answer the following questions (20 points total, 2
MAE112 Homework #1 Solutions
Jie Zhu
January 21, 2017
1
Problem 1
Total energy from detonation is E. Total kinetic energy input to the system is t E, which is given to the two masses.
Initially the two spheres are stationary. Lets say m gains velocity v a
MAE 112 Midterm #2 Mar. 2, 2016
2:00-2:50pm, closed-book, 4 letter-size, double-sided sheets of notes allowed.
No electronic devices of any kind is allowed.
Total 35 points.
Name:
Student ID:
Problem 1: Answer the following questions (20 points total, 2 p
MAE112 Homework #2 solution
Jie Zhu
February 4, 2017
1
Problem1
Applying Bernoullis equation at upstream and downstream
1
1
p + u2 = pa + u2m
2
2
where p
(1.1)
1
1
p + u2e = pb + u2m
2
2
is ambient pressure. Subtract equation 1.2 by 1.1
pb pa =
(1.2)
1
u
MAE112 Homework 5 solution
March 6, 2017
1
Problem 5.11
This problem is to calculate the take-off thrust, which means u = 0.
For turbojet
Ttj = m
a ue
Exhaust velocity in turbojet engine is
ue =
q
2cp (T05 Te )
And there is another useful relation (turbi
MAE 112 Final Exam Mar. 18, 2016
1:30-3:30pm, closed-book, 6 letter-size, double-sided sheets of notes allowed.
No electronic devices of any kind is allowed.
Total 40 points.
Name:
Student ID:
Problem 1: Answer the following questions (20 points total, 2
MAE 112 Midterm #2 Mar. 2, 2016
2:00-2:50pm, closed-book, 4 letter-size, double-sided sheets of notes allowed.
No electronic devices of any kind is allowed.
Total 35 points.
Name:
Student ID:
Problem 1: Answer the following questions (20 points total, 2 p
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
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