Loose Leaf for Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259683992
Author: Anderson, John
Publisher: McGraw-Hill Education
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Chapter 4, Problem 4.16P
For the conditions given in Problem 4.15, a more reasonable calculation of the skin friction coefficient would be to assume an initially laminar boundary layer starting at the leading edge. and then transitioning to a turbulent boundary layer at some point downstream. Calculate the skin-friction coefficient for the Spitfire’s airfoil described in Problem 4.15, but this time assuming a critical Reynolds number of
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The thin-walled open cross section shown is transmitting torque 7. The angle of twist ₁ per unit length of each leg can be
determined separately using the equation
01
=
3Ti
GLIC
3
where G is the shear modulus, ₁ is the angle of twist per unit length, T is torque, and L is the length of the median line.
In this case, i = 1, 2, 3, and T; represents the torque in leg i. Assuming that the angle of twist per unit length for each
leg is the same, show that
T= Lic³ and Tmaz = G01 Cmax
Consider a steel section with Tallow = 12.40 kpsi.
C1
2 mm
L1
20 mm
C2
3 mm
L2
30 mm
C3
2 mm
L3
25 mm
Determine the torque transmitted by each leg and the torque transmitted by the entire section.
The torque transmitted by the first leg is |
N-m.
The torque transmitted by the second leg is
N-m.
The torque transmitted by the third leg is
N-m.
The torque transmitted by the entire section is
N-m.
Chapter 4 Solutions
Loose Leaf for 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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