Fox And Mcdonald's Introduction To Fluid Mechanics
9th Edition
ISBN: 9781118921876
Author: Pritchard, Philip J.; Leylegian, John C.; Bhaskaran, Rajesh
Publisher: WILEY
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Textbook Question
Chapter 9, Problem 24P
Using numerical results obtained by Blasius (Table 9.1, on the web), evaluate the vertical component of velocity in a laminar boundary layer on a flat plate. Plot υ/U versus y/δ for Rex = 105.
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calculate drag force
B) for the velocity profiles given below, state whether the boundary layer has separated or on the verge of
separation or will remain attached (
i) u/U=2(y/8) -(y/8)² ii) u/U=-2(y/8) +0.5(y/8)³
iii) u/U-1.5(y/8) +0.5(y/8)³
Q3: Find the displacement, momentum thickness and energy thickness for the velocity distribution in the
boundary layer: F
u/U=0.5(y/8) + 1.5(y/8)³
Q4: A) Find the velocity distribution and expression of the maximum velocity and shear stress for a flow
between two stationary plates. C
B) A laminar flow of oil between two horizontal fixed parallel plates with a maximum velocity 2 m/s and
100mm apart. Canulate the pressure gradient and shear stress. Take µ-2.4525 s/m².
Reference 12 contains inviscid theory calculations for the
upper and lower surface velocity distributions V(x) over an
airfoil, where x is the chordwise coordinate. A typical re-
sult for small angle of attack is as follows:
xlc
VIU„(upper)
VIU„(lower)
0.0
0.0
0.0
0.025
0.97
0.82
0.05
1.23
0.98
0.1
1.28
1.05
1.13
0.2
1.29
0.3
1.29
1.16
0.4
1.24
1.16
0.6
1.14
1.08
0.8
0.99
0.95
1.0
0.82
0.82
Use these data, plus Bernoulli's equation, to estimate
(a) the lift coefficient and (b) the angle of attack if the
airfoil is symmetric.
Chapter 9 Solutions
Fox And Mcdonald's Introduction To Fluid Mechanics
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