Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259129919
Author: John D. Anderson Jr.
Publisher: McGraw-Hill Education
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Textbook Question
Chapter 5, Problem 5.3P
The measured lift slope for the NACA 23012 airfoil is 0.1080 degree
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Problem 13:
F₁ =
A
=250 N 30%
Determine the moment of each of the three forces about point B.
F₂ = 300 N
60°
2 m
-3 m
B
4 m
F3=500 N
3 kN
3 kN
1.8 kN/m
80 mm
B
300 mm
D
an
1.5 m-1.5 m--1.5 m-
PROBLEM 5.47
Using the method of Sec. 5.2, solve Prob. 5.16
PROBLEM 5.16 For the beam and loading shown, determine the
maximum normal stress due to bending on a transverse section at C.
300 mm
3 kN
3 kN
450 N-m
D
E
200 mm
300 mm
PROBLEM 5.12
Draw the shear and bending-moment diagrams for the beam and loading
shown, and determine the maximum absolute value (a) of the shear,
(b) of the bending moment.
Chapter 5 Solutions
Fundamentals of Aerodynamics
Ch. 5 - Consider a vortex filament of strength in the...Ch. 5 - Consider the same vortex filament as in Problem...Ch. 5 - The measured lift slope for the NACA 23012 airfoil...Ch. 5 - The Piper Cherokee (a light, single-engine general...Ch. 5 - Consider the airplane and flight conditions given...Ch. 5 - Consider a finite wing with an aspect ratio of 6....Ch. 5 - Repeat Problem 5.6, except for a lower aspect...Ch. 5 - In Problem 1.19 we noted that the Wright brothers,...Ch. 5 - Consider the Superrnarine Spitfire shown in Figure...Ch. 5 - If the elliptical wing of the Spitfire in Problem...
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