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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Chapter 12, Problem 36P
A supersonic wind tunnel test section is designed to have M = 2.5 at 15°C and 35 kPa absolute. The fluid is air. Determine the required inlet stagnation conditions, T0 and p0. Calculate the required mass flow rate for a test section area of 0.175 m2.
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The link lengths, gear ratio (2), phase angle (Ø), and the value of 02 for some geared five bar
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method. Show your work in details: vector loop, vector equations, solution procedure.
Table 2
Row
Link 1 Link 2
Link 3
Link 4
Link 5
λ
Φ
Ө
a
6
1
7
9
4
2
30°
60°
P
y 4
YA
B
b
R4
R3
YA
A
Gear ratio:
a
02
d
05
r5
R5
R2
Phase angle: = 0₂-202
R1
05
02
r2
Figure 2.
04
X
Problem 4
A .025 lb bullet C is fired at end B of the 15-lb slender bar AB. The
bar is initially at rest, and the initial velocity of the bullet is 1500 ft/s
as shown. Assuming that the bullet becomes embedded in the bar,
find (a) the angular velocity @2 of the bar immediately after impact,
and (b) the percentage loss of kinetic energy as a result of the impact.
(c) After the impact, does the bar swing up 90° and reach the
horizontal? If it does, what is its angular velocity at this point?
Answers: (a). @2=1.6 rad/s; (b). 99.6% loss
=
(c). Ah2 0.212 ft. The bar does not reach horizontal.
y
X
4 ft
15 lb
V₁
1500 ft/s
0.025 lb
C
30°7
B
A
subject: combustion
please include complete solution, no rounding off, with diagram/explanation etc.
In a joule cycle, intake of the compressor is 40,000 cfm at 0.3 psig and 90 deg F. The compression ratio is 6.0 and the inlet temperature at the turbine portion is 1900R while at the exit, it is 15 psi. Calculate for the back work ratio in percent.
Chapter 12 Solutions
Fox And Mcdonald's Introduction To Fluid Mechanics
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