Anderson P9.14) Con sider a diamondwed ge airfoil with a halfan gle e = 10. The airfoil is an angle
of attack a = 15 to a Mach 3 freestream . Ca lculate the lift and wavedrag coefficients for the airfoi l.
(j)
t. ';
/0 "
"=1
J) s
./vl~ : '3.;) 5
= )
Anderson P9.10 ) Consider the supersonic flow over an expan sio n corner. The deflection angle e =
23.38, If the flow upstr eam of the corner is give n by M, = 2, Pl = 0.7 atm, T L = 400K, ca lculate M2 , P2,
T2, P2, PO.2, and To.2 downstr eam of the corn
Anderson P9.8) Cons ider a Mach 4 airfl ow at a pressure of 1 atm. We wish to slow this flow to
subsonic speed thr ough a system of shock waves with as small a loss in total pressure as possible.
Compare the loss in total pressur e for the following thr e
Anderson P 7.3) Ju st upstream of a shock wave, the air temp eratur e and pressure are 288 K and I atm,
respectively ; j ust downst ream of the wave, the air tem perature and pressure are 690 K and 8.656 atm,
respectively. Ca lculate the changes in entha
Anderson P9.12) A supersonic flow at M 1 = 3, T, = 285K, and Pi = 1 atm is det1ected upward through
a compression corner with = 30.6 and then is subsequently expanded around a corner of the same
angle such that the flow direction is the same as its origin
Anderson P7.9) An airfoil is in a frees trea m where P>
0.6 1 atrn, p"
=
= 0.8 19 kg/m 3, and
V,
=
300
mJs. At a point on the airfoi l surface, the pressure is 0.5 atm. Assuming isentropic flow, calculate the
velocity at that point.
"PCP' : 0
I
I o~4v. .
Anderson P9.5) Consider the flow ove r a 22. 2 0 halfangle wedge . If M I = 2.5, Pi = I attn, and TI =
300 K, calcul ate the wave ang le and P2, T2, and M2 .
j vt , = :;cfw_ . 5
~ :
"?
M

I
J
I
o~+
.
"' J
r'
J
I,
.M ,
.'
M"
<cfw_J "'
'I
"; :)
I
~)
Anderson P5.3) The measured lift slope for the NACA 23012 airfoil is 0.1080 degree: ', and OL O =
1.3 . Consider a finite wing using the airfoil, with AR = 8 and taper ratio = 0.8. Assume that r5 = T,
where (5 is related to the span efficiency factor e
Anderson P9.6 ) Consider a t1at plate at an angle of attac k cfw_J. to a Mach 2.4 airflow at 1 atm pressur e.
What is the maximum pressure that can occ ur on the plate surface and still have an attached s ho;~a ve
at the leading edge? At what va lue of (J
SAMPLE (/2 46/7 CE 196019219211
Problems taken from Chapter 11 of Fluid Mechanics by White
P1116 The centrifugal pump in Fig. P11.16 has r1 t 15 cm, 1'; = 25 cm, 191 = b: =
6 cm, and rotates counterclockwise at 600 r/miu. A sample blade is shown. Assume 0
ME 563 Sample Problems Wind Turbines
March 27, 2017
1) Ideal Rotor Section Analysis
a. Find , P, Tip, and c for one blade section from r/R = 0.45 to r/R = 0.55 (centered on r/R
= 0.50) for an ideal blade (assume Cd = 0, a = 0). Assume =7, Nblades=3, R=5 m
ME 563 Axial Fan examples
(from Fundamentals of Turbomachines, Dick)
Axial Fan (Idealised Flow): Analysis on Average Diameter
The rotor of an axial fan has a hub diameter dh = 0.24 m and a tip diameter dt = 0.48 m.
There is no preswirl. The inlet flow is
A small pump with an impeller diameter of 9 cm operates at 3450 rpm. It is a backward facing
design with an exit blade angle of 25 degrees. Exit radial velocity is 3.0 m/s. The entry axial
velocity is 4.13 m/s at the inlet radius of 2.8 cm.
a) Using Euler
A
2010 2011 1
_ _
Production and Operations Analysis
_
_
1. A simple forecasting method for weekly sales of DVD derives used by a local computer dealer
is to form the average of the two most recent sales figures. Suppose sales for the drives for the
Problem Set #5
ME322 Mechanical Design I
Mechanical and Mechatronics Engineering Department
University of Waterloo
Problem 1: The cantilevered bar in the gure is made from a ductile material and is statically loaded
with Fx = 75 lbf, Fy = 200 lbf, and Fz
Problem Set 1
ME322 Mechanical Design I
Mechanical and Mechatronics Engineering Department
University of Waterloo
Solutions will be posted after tutorials
Problems 1 to 4: For the beams shown, nd the reactions at the supports and plot the shearforce and
Problem Set #4
ME322 Mechanical Design I
Mechanical and Mechatronics Engineering Department
University of Waterloo
Solutions will be posted after tutorials
Problem 1 (334): For each section illustrated, find the second moment of area, the location of th
Problem Set #3
ME322 Mechanical Design I
Mechanical and Mechatronics Engineering Department
University of Waterloo
Solutions will be posted after tutorials
3
4
Problem 1 (323): A indiameter steel tension rod is 5 ft long and carries a load of 15 kip.
Problem Set 2
ME322 Mechanical Design I
Mechanical and Mechatronics Engineering Department
University of Waterloo
Solutions will be posted after tutorials
Problem 1: For each of the plane stress states listed below, draw a Mohr's circle diagram properly
Problem Set #8 Solution
P1
(a) Thread depth= 2.5 mm Ans.
Width = 2.5 mm Ans.
dm = 25  1.25  1.25 = 22.5 mm
dr = 25  5 = 20 mm
l = p = 5 mm Ans.
(b) Thread depth = 2.5 mm Ans.
Width at pitch line = 2.5 mm Ans.
dm = 22.5 mm
dr = 20 mm
l = p = 5 mm Ans.
Problem Set #9 Solution
Problem 1
2 (100 ) (103 )
2F
= =
= 141 MPa
Ans.
hl
5 2 ( 50 + 50 )
_
Problem 2
b = d =50 mm, c = 150 mm, h = 5 mm, and allow = 140 MPa.
(a) Primary shear, Table 91, Case 2 (Note: b and d are interchanged between
problem figure an
Assignment #62 Solution
P1
From a freebody diagram analysis, the bearing reaction forces are found to be 2.1 kN at the left
bearing and 3.9 kN at the right bearing. The critical location will be at the shoulder fillet
between the 35 mm and the 50 mm di
Problem Set #7 Solution
P1
F cos 20(d / 2) = TA, F = 2 TA / ( d cos 20) = 2(340) / (0.150 cos 20) = 4824 N.
The maximum bending moment will be at point C, with MC = 4824(0.100) = 482.4 Nm.
Due to the rotation, the bending is completely reversed, while th
Problem Set #4 Solution
Problem 1:
(a)
Let a = total area of entire envelope
Let b = area of side notch
A = 2b =
a
40(2)(37.5) 25 ( 34 ) =
2150 mm 2
1
1
3
3
I = a 2 I b = ( 40 )( 75 ) ( 34 )( 25 )
I
12
12
6
4
I = 1.36 (10 ) mm
Ans.
Dimensions in mm.
(b)
A
Problem Set #5 Solution
Problem 1:
(a)
Rod AB experiences constant torsion and constant axial tension throughout its length, and
maximum bending moments at the wall from both planes of bending. Both torsional shear stress and
bending stress will be maximu
Problem Set #3 Solution
Problem 1:
F
=
A
=
15000
= 33 950 psi 34.0 kpsi
=
( 4 ) ( 0.752 )
FL
L
60
= = 33 950
= 0.0679 in
AE
E
30 (106 )
=
1
=
=
L
0.0679
= 1130 (106 = 1130
)
60
Ans.
Ans.
Ans.
From Table A5, v = 0.292
2 = 1 =
v
0.292(1130) =
330
Ans.
d
Problem Set 1  Solution
Problem 1
M C =
0
1500 R1 + 300(5) + 1200(9) =
0
R1 = 8.2 kN Ans.
Fy =
0
8.2 9 5 + R2 =
0
R2 = 5.8 kN
Ans.
= 8.2(300) 2460 N m Ans.
M1
=
M 2 = 0.8(900) = N m Ans.
2460
1740
M 3 = 5.8(300) =checks!
1740
0
_
Problem 2
0
Fy =
RO = +