Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259129919
Author: John D. Anderson Jr.
Publisher: McGraw-Hill Education
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Textbook Question
Chapter 4, Problem 4.15P
The airfoil section of the wing of the British Spitfire of World War II fame (see Figure 5.19) is an NACA 2213 at the wing root, tapering to an NACA 2205 at the wing tip. The root chord is 8.33 ft. The measured profile drag coefficient of the NACA 2213 airfoil is 0.006 at a Reynolds number of
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H.W 5.4
Calculate the load that will make point A move to the left by 6mm, E-228GPa. The diameters
of the rods are as shown in fig. below.
2P-
PA
50mm
B
200mm
2P
0.9m
1.3m
d₁
=
=
Two solid cylindrical road AB and
BC are welded together at B and
loaded as shown. Knowing that
30mm (for AB) and d₂
50mm (for BC), find the average
normal stress in each road and the
total deformation of road AB and
BC. E=220GPa
H.W 5.3
60kN
A
For the previous example calculate the
value of force P so that the point A will not
move, and what is the total length of road
AB at that force?
P◄
A
125kN
125kN
0.9m
125kN
125kN
0.9m
B
B
1.3m
1.3m
Class:
B
Calculate the load that will make point A move to the left by 6mm, E-228GPa
The cross sections of the rods are as shown in fig. below.
183
P-
Solution
1.418mm
200mm
80mm
3P-
18.3
A
080mm
B
200mm
3P-
0.9m
إعدادات العرض
1.3m
4.061mm
Chapter 4 Solutions
Fundamentals of Aerodynamics
Ch. 4 - Consider the data for the NACA 2412 airfoil given...Ch. 4 - Consider an NACA 2412 airfoil with a 2-m chord in...Ch. 4 - Starting with the definition of circulation,...Ch. 4 - Starting with Equation (4.35), derive Equation...Ch. 4 - Consider a thin, symmetric airfoil at 1.5 angle of...Ch. 4 - The NACA 4412 airfoil has a mean camber line given...Ch. 4 - For the airfoil given in Problem 4.6, calculate...Ch. 4 - Compare the results of Problems 4.6 and 4.7 with...Ch. 4 - Starting with Equations (4.35) and (4.43), derive...Ch. 4 - For the NACA 2412 airfoil, the lift coefficient...
Ch. 4 - Consider again the NACA 2412 airfoil discussed in...Ch. 4 - For the airfoil in Problem 4.11, calculate the...Ch. 4 - In Section 3.15 we studied the case of the lifting...Ch. 4 - The question is often asked: Can an airfoil fly...Ch. 4 - The airfoil section of the wing of the British...Ch. 4 - For the conditions given in Problem 4.15, a more...
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