University of Turkish Aeronautical Association  Merkez Campus
Aircraft Structures
AERONAUTIC 362

Spring 2016
Prof. Daniel J. Bodony
AE433, Fall 2015
HW #5
Due 30 October 2015 in class
Problem 1 Recall from class that the thermal efficiency of an ideal turbojet engine is T = 1 (r c )1 . This
efficiency can be maximized by adjusting the compressor pressure ratio a
University of Turkish Aeronautical Association  Merkez Campus
Aircraft Structures
AERONAUTIC 362

Spring 2016
Prof. Daniel J. Bodony
AE433, Fall 2015
HW #6
Due 9 November 2015 in class
Problem 1 (This problem should help clear up any residual confusion from HW5.) Consider an ideal turbofan with
separate exhaust streams. Assuming the following properties are known
University of Turkish Aeronautical Association  Merkez Campus
Aircraft Structures
AERONAUTIC 362

Spring 2016
Prof. Daniel J. Bodony
AE433, Fall 2015
HW #4
Due 21 October 2015 in class
Problem 1
In class we showed that the specific thrust of an ideal turbojet engine could be written
"
#1/2
F
2
(r c t 1)
=
M0 .
m
0 a0
1 r c
(a) Using the power balance between
University of Turkish Aeronautical Association  Merkez Campus
Aircraft Structures
AERONAUTIC 362

Spring 2016
Energy methods:
These are methods based on linear elastic behavior and conservation of energy, i.e. the
work done by external forces equals the energy stored in the structure under load.
Energy U = Fx/2 = F2/2k where F is the applied force, x is the dista
University of Turkish Aeronautical Association  Merkez Campus
Aircraft Structures
AERONAUTIC 362

Spring 2016
COMPLEX STRESS
TUTORIAL 5
STRAIN ENERGY
This tutorial covers parts of the Engineering Council Exam D210 Structural
Analysis and further material useful students of structural engineering.
You should judge your progress by completing the self assessment ex
University of Turkish Aeronautical Association  Merkez Campus
Aircraft Structures
AERONAUTIC 362

Spring 2016
QUESTION :
Consider the rectangular, uniform crosssection wing structure given below. Wing is subjected to a
triangular lift (W(x); N/m) and pitching moment distribution (T(x); Nm/m) such that the root values
are Wo and To, respectively. Distributed lift
University of Turkish Aeronautical Association  Merkez Campus
Aircraft Structures
AERONAUTIC 362

Spring 2016
AEE 362 2013 Spring
Homework 3
Homework Due: Friday April 5, 2013
Section: _ Name: _
COVER SHEET
HW is to be turned in with the cover sheet filled out and signed.
HW is due before class one week after it is handed out.
Use the systematic solution techniqu
University of Turkish Aeronautical Association  Merkez Campus
Aircraft Structures
AERONAUTIC 362

Spring 2016
AEE 362
20152
HW2 Solution
1a. In this part of the question, it is expected to derive lateral displacement of the beam by
using the unit load method. Although only shear force affects the lateral displacement, there
will not be a point reduction from the
University of Turkish Aeronautical Association  Merkez Campus
Aircraft Structures
AERONAUTIC 362

Spring 2016
AE362 Aerospace Structures
Due Date: March 30, 2016
Homework #2
1) (a) For a beam subjected to lateral forces derive an expression for the lateral displacement at point
in the rectangular crosssection beam by using the unit load method.
(b) Determine th