BASIC EQUATIONS FOR ONE-DIMENSIONAL FLOW (Chapter 04)

CHAPTER 4
BASIC EQUATIONS FOR ONE-DIMENSIONAL FLOW
4.1. EULER’S EQUATION OF MOTION
Consider a streamline and select a small cylindrical fluid system for analysis as shown
in Fig. 4.1.
V ds
V
P1
1
1
P
dA
p + dp
V + dV
z
dz
2
P
2V
2
dW = ρg ds dA
Horizontal datum plane
Fig. 4.1
The forces tending to accelerate the cylindrical fluid system are: forces on the ends of
the system,
( ) dpdAdAdpppdA −=+−
and the component of weight in the direction of motion,
gdAdz
ds
dz
gdsdA ρρ −=−
The differential mass being accelerated by the action of these differential forces is,
dsdAdm ρ=
Applying Newton’s second law dF = dm×a along the streamline and using the one-
dimensional expression for acceleration gives
( )
ds
dV
VdsdAgdAdzdpdA ρρ =−−
Prof. Dr. Atıl BULU49

Dividing by ρdA produces the one dimensional Euler equation,
0=++ gdzVdV
dp
ρ
This equation is divided by g and written
0
2
2
=⎟⎟
⎠
⎞
⎜⎜
⎝
⎛
++ z
g
Vp
d
γ
4.2. BERNOULLI’S EQUATION
The one-dimensional Euler equation can be easily integrated between any points
(because γ and g are both constants) to obtain
2
2
22
1
2
11
22
z
g
Vp
z
g
Vp
++=++
γγ
As points 1 and 2 are any two arbitrary points on the streamline, the quantity
==++ Hz
g
Vp
2
2
γ
Constant (4.1)
Applies to all points on the streamline and thus provides a useful relationship between
pressure p, the magnitude V of the velocity, and the height z above datum. Equ. (4.1) is
known as the Bernoulli equation and the Bernoulli constant H is also termed the total head.
Examination of the Bernoulli terms of Equ. (4.1) reveals that p/γ and z are
respectively, the pressure (either gage or absolute) and potential heads and may be visualized
as vertical distances. The sum of velocity head V2
/2g and pressure head p/γ could be
measured by placing a tiny open tube in the flow with its open end upstream. Thus Bernoulli
equation may be visualized for liquids as in Fig. 4.2, the sum of the terms (total head) being
the constant distance between the horizontal datum plane and the total headline or energy line
(E.L.). The piezometric head line or hydraulic grade line (H.G.L.) drawn through the tops of
the piezometer columns gives a picture of the pressure variation in the flow; evidently
1) Its distance from the stream tube is a direct measure of the static pressure in the
flow,
2) Its distance below the energy line is proportional to the square of the velocity.

z
Total
head, H
E.L.
H.G.L.
P
γ
V /2g
2
dA
P
V
Fig. 4.2
4.3. MECHANICAL ENERGY OF A FLOWING FLUID
An element of fluid, as shown in Fig. 4.3, will posses potential energy due to its height
z above datum and kinetic energy due to its velocity V, in the same way as any other object.
z
Datum level
Cross-sectional
area A
A
mg A'
V
ρ B
B'
Fig. 4.3
For an element of weight mg,
Potential energy = mgz
Potential energy per unit weight = z (4.2)
Kinetic energy = 2
2
1
mV
Kinetic energy per unit weight =
g
V
2
2
(4.3)

A steadily flowing stream of fluid can also do work because of its pressure. At any
given cross-section, the pressure generates a force and, as the fluid flows, this cross-section
will move forward and so work will be done. If the pressure at section AB is p and the area of
the cross-section is A,
Force exerted on AB = pA
After a weight mg of fluid has flowed along the stream tube, section AB will have
moved to A’B’:
Volume passing AB =
ρρ
m
g
mg
=
Therefore,
Distance AA’ =
A
m
ρ
Work done = Force×Distance AA’
A
m
pA
ρ
×=
Work done per unit weight =
γρ
p
g
p
= (4.4)
The term p/γ is known as the flow work or pressure energy. Note that term pressure
energy refers to the energy of a fluid when flowing under pressure. The concept of pressure
energy is sometimes found difficult to understand. In solid body mechanics, a body is free to
change its velocity without restriction and potential energy can be freely converted to kinetic
energy as its level falls. The velocity of a stream of fluid which has a steady volume rate of
flow (discharge) depends on the cross-sectional area of the stream. Thus, if the fluid flows in
a uniform pipe, its velocity cannot change and so the conversion of potential energy to kinetic
energy cannot take place as the fluid loses elevation. The surplus energy appears in the form
of an increase in pressure. As a result, pressure energy can be regarded as potential energy in
transit.
Comparing the results obtained in Eqs. (4.2), (4.3) and (4.4) with Equ. (4.1), it can be
seen that the three terms Bernoulli’s equation are the pressure energy per unit weight, the
kinetic energy per unit weight, and the potential energy per unit weight; the constant H is the
total energy per unit weight. Thus, Bernoulli’s equation states that, for steady flow of a
frictionless fluid along a streamline, the total energy per unit weight remains constant from
point to point although its division between the three forms of energy may vary:
Pressure Kinetic Potential Total
energy per + energy per + energy per = energy per = Constant
unit weight unit weight unit weight unit weight
Hz
g
Vp
=++
2
2
γ
(4.5)

Each of these terms has the dimensions of a length, or head, and they are often referred
to as the pressure head p/γ, the velocity head V2
/2g, the potential head z and the total head H.
Between any two points, suffixes 1 and 2, on a streamline, Equ. (4.5) gives
2
2
22
1
2
11
22
z
g
Vp
z
g
Vp
++=++
γγ
(4.6)
or
Total energy per unit weight at 1 = Total energy per unit weight at 2
In formulating Equ. (4.6), it has been assumed that no energy has been supplied to or
taken from the fluid between points 1 and 2. Energy could have been supplied by introducing
a pump; equally, energy could have been lost by doing work against friction in a machine
such as a turbine. Bernoulli’s equation can be expanded to include these conditions, giving
Total energy Total energy Loss Per Work done Energy
per unit = per unit + unit + per unit - supplied per
weight at 1 weight at 2 weight weight unit weight
EXAMPLE 4.1: A fire engine develops a head of 50 m, i.e., it increases the energy
per unit weight of the water passing through it by 50 m. The pump draws water from a sump
at A through a 150 mm diameter pipe in which there is a loss of energy per unit weight due to
friction h1 = 5V1
2
/2g varying with the mean velocity V1 in the pipe, and discharges it through
a 75 mm nozzle at C, 30 m above the pump, at the end of a 100 mm diameter delivery pipe in
which there is a loss of energy per unit weight h2 = 12V2
2
/2g. Calculate,
a) The velocity of the jet issuing from the nozzle at C,
b) The pressure in the suction pipe at the inlet to the pump at B.
Pump
3
Z =2 m2
A
Jet velocity , V
Jet diameter , d3
Pipe velocity , V
Pipe diameter , d = 100 mm
Delivery pipe loss = 12 V / 2g
2
Pipe velocity , V
Pipe diameter , d = 150 mm
Delivery pipe loss = 5V / 2g
1
C
B
Datum level
3
2
2
2
1
1
1
2
z
Fig.4.4

SOLUTION:
a) We can apply Bernoulli’s equation in the form of Equ. (4.6) between two points, one
of which will be C, since we wish to determine the jet velocity V3, and the other point
at which conditions are known, such as a point A on the free surface of the sump
where the pressure will be atmospheric, so that pA = 0, the velocity VA will be zero if
the sump is large, and A can be taken as datum level so that zA = 0. Then,
Total energy Total energy Loss in Energy per unit Loss in
per unit = per unit + inlet - weight supplied + discharge (I)
weight at A weight at C pipe by pump pipe
Total energy
per unit = 0
2
2
=++ A
AA
z
g
Vp
γ
weight at A
Total energy
per unit = 3
2
3
2
z
g
VpC
++
γ
weight at C
pC = Atmospheric pressure = 0
mz 322303 =+=
Therefore,
Total energy
per unit = 32
2
32
2
0
2
3
2
3
+=++
g
V
g
V
weight at C
Loss in inlet pipe,
g
V
h
2
5
2
1
1 =
Energy per unit weight supplied by pump = 50 m
Loss in delivery pipe,
g
V
h
2
12
2
2
2 =
Substituting in (I),
g
V
g
V
g
V
2
1250
2
532
2
0
2
2
2
1
2
3
+−++=
182125 2
2
2
1
2
3 ××=++ gVVV (II)

From the continuity of flow equation,
3
2
3
2
2
2
1
2
1
444
V
d
V
d
V
d πππ
==
Therefore,
33
2
3
2
2
3
2
33
2
3
2
1
3
1
16
9
100
75
4
1
150
75
VVV
d
d
V
VVV
d
d
V
=⎟
⎠
⎞
⎜
⎝
⎛
=⎟⎟
⎠
⎞
⎜⎜
⎝
⎛
=
=⎟
⎠
⎞
⎜
⎝
⎛
=⎟⎟
⎠
⎞
⎜⎜
⎝
⎛
=
Substituting in Equ. (II),
12
16
9
12
4
1
51
22
2
3 ××=
⎥
⎥
⎦
⎤
⎢
⎢
⎣
⎡
⎟
⎠
⎞
⎜
⎝
⎛
+⎟
⎠
⎞
⎜
⎝
⎛
+ gV
sec31.8
182109.5
3
2
3
mV
gV
=
××=
b) If pB is the pressure in the suction pipe at the pump inlet, applying Bernoulli’s
equation to A and B,
Total energy Total energy Loss in
per unit = per unit + inlet
weight at A weight at B pipe
g
V
z
p
g
V
z
g
Vp
B
B
2
6
2
5
2
0
2
1
2
2
1
2
2
1
−−=
+++=
γ
γ
mz 22 = , sec08.2
4
31.8
4
1
31 mVV ===
m
g
pB
32.3
2
08.2
62
2
−=−−=
γ
2
32.3132.3 mtpB −=×−= (below atmospheric pressure)

4.4. THE WORK-ENERGY EQUATION
The application of work-energy principles to fluid results in a powerful relationship
between fluid properties, work done, and energy transported. The Bernoulli equation is then
seen to be equivalent to the mechanical work-energy equation for ideal fluid flow.
P , ρ
V
V
1
1
ds
I
1
1
ds
OdA
ρ , P2
2
2
2
2
2
2
1
1
1
z
z
Fig. 4.5
Consider the differential stream tube section shown in Fig. 4.5 and the fluid system
that occupies zones I and R of the control volume 1221 at time t and zones R and O at time
t+dt. For steady flow the continuity Equ. (3.8) gives
2211 VdAVdA = or 2211 dsdAdsdA =
From dynamics, the mechanical work-energy relation (which is only an integrated
form of Newton’s second law) states that the work dW (expressed as a force acting over a
distance) done on a system produces an equivalent change in the sum of the kinetic (KE) and
potential (PE) energies of the system, that is, in time dt
dW = d(KE+PE) = (KE+PE)t+dt – (KE+PE)t
Now
(KE+PE)t = (KE+PE)R + (KE+PE)I
(KE+PE) t = (KE+PE) R + ( ) ( 111
2
111
2
1
zdsdAVdsdA γρ + )
(KE+PE) t+dt = (KE+PE) R + (KE+PE) O
(KE+PE) t+dt = (KE+PE) R + ( ) ( 222
2
222
2
1
zdsdAVdsdA γρ + )
Because kinetic energy of translation is mV2
/2 and potential energy is equivalent to
the work of raising the weight of fluid in a zone to a height z above the datum.

The external work done on the system is all accomplished on cross sections 11 and 22
because there is no motion perpendicular to the stream tube so the lateral pressure forces can
do no work. Also because all internal forces appear in equal and opposite pairs, there is no
network done internally. The work done by the fluid entering I on the system in time dt is the
flow work.
( ) 111 dsdAp
As the system does work on the fluid in time O in time dt, the work done on the
system is
( ) 222 dsdAp−
In sum then
( ) ( ) ( ) ( ) ( ) ( 111
2
111222
2
222222111
2
1
2
1
zdsdAVdsdAzdsdAVdsdAdsdApdsdAp γργρ −−+=− )
Dividing by dA1ds1 = dA2ds2 produces
1
2
12
2
221
2
1
2
1
zVzVpp γργρ −−+=−
When rearranged, this is recognized as Bernoulli’s equation,
2
2
22
1
2
11
22
z
g
Vp
z
g
Vp
++=++
γγ
(4.7)
Which can be interpreted now as a mechanical energy equation. Terms such as p1/γ,
V1
2
/2g, z have the units of meters which represent energy per unit weight of fluid.
4.5. KINETIC ENERGY CORRECTION FACTOR
The derivation of Bernoulli’s equation has been carried out for a stream tube assuming
a uniform velocity across the inlet and outlet sections. In a real fluid flowing in a pipe or over
a solid surface, the velocity will be zero at the solid boundary and will increase as the distance
from the boundary increases. The kinetic energy per unit weight of the fluid will increase in a
similar manner. If the cross-section of the flow is assumed to be composed of a series of small
elements of area dA and the velocity normal to each element is u, the total kinetic energy
passing through the whole cross-section can be found by determining the kinetic energy
passing through an element in unit time and then summing by integrating over the whole area
of the section,
Kinetic energy ∫∫∫ ===
AAA
dAu
dt
udtdA
u
dm
u 3
22
222
ρ
ρ

Which can be readily integrated if the exact velocity is known. It is, however, more
convenient to express the kinetic energy in terms of average velocity V at the section and a
kinetic energy correction factor α such that
K.E. 3
2
22
AV
dt
m
V ρ
αα ==
In which m = ρAVdt is the total mass of the fluid flowing across the cross-section
during dt. By comparing the two expressions for kinetic energy, it is obvious that
∫=
A
dAu
AV
3
3
1
α (4.8)
Mathematically, the cube of the average is less than the average of cubes, that is,
∫<
A
dAu
A
V 33 1
The numerical value of α will always be greater than 1. Then Equ. (4.6) takes the form
of Equ. (4.9) by taking kinetic energy correction factor, α, as
2
2
2
2
2
1
2
1
1
1
22
z
g
Vp
z
g
Vp
++=++ α
γ
α
γ
(4.9)
The factor α depends on the shape of the cross-section and the velocity distribution. In
most engineering problems of turbulent flow in circular pipes, α has a numerical value
ranging from 1.01 to 1.10. Here α can be assumed to be unity without introducing any serious
error.
The energy equation (Equ.4.9) for the flow system becomes
2
2
22
1
2
11
22
z
g
Vp
z
g
Vp
++=++
γγ
(4.7)
Which is identical to the energy equation for fluid flow along a streamline.
4.6. APPLICATIONS OF BERNOULLI’S EQUATION
Although there is always some friction loss in the flow of real fluids, in many
engineering problems the assumption of frictionless flow may yield satisfactory results.
An important feature of Bernoulli’s equation is in its graphical representation of the
three terms, p/γ, z, and V2
/2g, at each section of the flow system. In Fig. 4.6 there is shown a
typical example of steady flow of an ideal fluid from a large reservoir through a system of
pipes varying in size and terminating in a nozzle.

Total energy line
Piezometric
line
Reservoir
P
γ
V
2g
2
V
2g
2
j
Vj
Fig. 4.6
Since the cross-sectional area of the reservoir is very large and there the velocity is
zero, both the total energy line and piezometric line coincide with the free surface in the
reservoir. The total energy line of the whole flow system must be horizontal if the flow is
assumed to be frictionless (ideal). The flow in the pipes at various sections follows the
continuity principle, that is, Q = VA. The volume rate of flow (discharge) Q can be
determined by writing Bernoulli’s equation to relate flow conditions at the free surface of the
reservoir and the jet at the nozzle outlet. Thus the velocity head V2
/2g at any section is
determined and, finally the piezometric line is sketched in at a distance of V2
/2g below the
total energy line. The distance between the piezometric line and the line of the pipe is the
pressure head p/γ at any section. If the piezometric line stays above the centerline of the pipe,
the pressure head is positive. Otherwise, negative pressure prevails throughout the region
where the piezometric line falls below the centerline of the pipe. Care must be taken in
dealing with the regions of negative pressure because of the adverse effect of cavitation, a
phenomenon closely associated with the regions where the local pressure drops to the vapor
pressure of the liquid flowing in the system. At the region of low pressure liquid tends to
vaporize and water bubbles start to form. These vapor bubbles are carried downstream and
subsequently collapse in the zones of higher pressure. The repeated collapsing of vapor
bubbles produces extremely high hydrodynamic pressures upon the solid boundaries,
frequently causing severe physical damages to the boundary material. In order to avoid
cavitation, it is essential to eliminate the zone of low pressure where vaporization may take
place. The position of the piezometric line yields visual information on the pressure
conditions of the whole flow system.
EXAMPLE 4.2: The 10 cm (diameter) siphon shown in Fig. 4.7 is filled with water
and discharging freely into the atmosphere through a 5 cm (diameter) nozzle. Assume
frictionless flow and find, a) the discharge in cubic meter per second and, b) the pressure at C,
D, E, and F.
SOLUTION:
a) Since the flow is assumed to be frictionless, Bernoulli’s equation (Equ. 4.6) can be
applied to points A and G with elevation datum at G and zero gage pressure as
pressure datum:
g
V
z
p
g
V
z
p G
G
GA
A
A
22
22
++=++
γγ

G
Piezometric
lineV
2g5m
10cm
D
F
P
γ
F
3m
DP
γ
P
γ
C A
C
D
Total energy line
P
γ
E
2
E
2
V
2g
5 cm
G
Fig. 4.7
Point A is at the reservoir surface where atmospheric pressure prevails and velocity is
negligible. Therefore,
sec0194.090.905.0
4
sec90.952
2
00050
32
2
mVAQ
mgV
g
V
GG
G
G
=××==
=×=
++=++
π
b) From the continuity equation the velocity in the 10 cm diameter siphon is,
sec48.2
10.0
0194.044
22
m
D
Q
A
Q
V =
×
×
===
ππ
By using the same elevation and pressure data as in (a) and writing Bernoulli’s
equation to relate flow conditions at A and C,
g
pC
2
48.2
5050
2
++=++
γ
from which
m
pC
31.0−=
γ
of water
2
31.0 mtpC −=
The minus sign indicates vacuum.
Similarly, between A and D
g
pD
2
48.2
8050
2
++=++
γ
m
pD
31.3−=
γ
of water
2
31.3 mtpD −=

Between A and E,
g
pE
2
48.2
5050
2
++=++
γ
m
pE
31.0−=
γ
of water
2
31.0 mtpE −=
Between A and F,
g
pF
2
48.2
0050
2
++=++
γ
m
pF
69.4=
γ
of water
2
69.4 mtpF =
The total energy line and piezometric line shown in Fig. 4.7 are self-explanatory.
4.6.1. Torricelli’s Theorem
The classical Torricelli’s theorem, which was formulated through experimentation,
states that the velocity of liquid flowing out of an orifice is proportional to the square root of
the height of liquid above the center of the orifice. This statement can readily be proved by
applying Bernoulli’s equation.
The reservoir in Fig. 4.8 is filled with a liquid of specific weight γ to a height h above
the center of a round orifice O in its side. It is assumed, 1) That both the free surface of the
liquid in the reservoir and the liquid jet are exposed to the atmospheric pressure, that is, pA =
p0; 2) That the liquid surface in the reservoir remains constant; and 3) That the surface area of
the reservoir is large compared with the cross-sectional area of the orifice. Thus the velocity
head at A may be neglected, that is, VA
2
/2g ≅ 0. Therefore, if the elevation at the center of the
orifice is taken as a datum, Bernoulli’s equation for flow conditions between A and O
becomes,
g
Vp
h
p oOA
2
00
2
++=++
γγ
or, solving for Vo,
ghVO 2= (4.10)
Which is known as Torricelli’s theorem. It is worth noting here that the velocity of efflux is
identical to the velocity attained in free fall.

A
h
OV
2g
2
VO
O
Fig. 4.8
EXAMPLE 4.3: The pressurized tank shown has a circular cross-section 2 m in
diameter. Oil is drained through a nozzle 0.08m in diameter in the side of the tank. Assuming
that the air pressure is maintained constant, how long does it take to lower the oil surface in
the tank by 2 m? The specific weight of the oil in the tank is 0.75 t/m3
and that of mercury is
13.6 t/m3
.
Compressed air
5 m
h
dh
B
A
Oil
8 cm
2 m
5 cm
Mercury
Fig. 4.9
SOLUTION: The pressure head in the tank above the oil surface is maintained at a
constant value of,
m
p
oil
A
91.0
75.0
6.13
05.0 =×=
γ
of oil
Since the oil surface drops constantly, the discharge out of the nozzle will vary with time. By
neglecting the friction loss, Bernoulli’s equation (Equ. 4.6) is written for flow conditions
between a point B in the oil when the oil surface is at a height h above the center of the nozzle
and the point j in the jet.

g
V
z
p
g
V
z
p j
j
oil
jB
B
oil
B
22
22
++=++
γγ
The cross-sectional area of the tank is very much larger than the jet area; VB is
approximately zero for all practical purposes. The jet issuing out of the nozzle is subject to the
atmospheric pressure. By choosing the center of the nozzle as the elevation datum and the
local atmospheric pressure as the pressure datum,
( )hgV
g
V
h
j
j
+=
++=++
91.02
2
00091.0
2
Which is the instantaneous velocity of the jet when the oil surface is at h above the
center of the nozzle.
From the continuity equation the total discharge out of the nozzle during a small
interval dt must be equal to the reduction in the volume of oil in the tank. Thus,
dhAdtVA tjj =
or
( ) dhdthg ××−=+× 22
2
4
91.0208.0
4
ππ
from which
( )∫∫
−
+−=
3
0
21
0
91.0
2
625
dhh
g
dt
t
By integrating
( )[ ] sec12891.02
2
625 3
5
21
=+−= h
g
t
4.6.2. Free Liquid Jet
A free liquid jet is actually a streamline along which the pressure is atmospheric.
Accordingly, Bernoulli’s equation may be applied to the whole trajectory of the jet if the air
resistance is neglected. With the pressure head p/γ equal to zero, the sum of velocity head and
elevation head above any arbitrarily chosen datum must remain constant for all points along
the trajectory (Fig. 4.10).

Trajectory
of
free jet
(υ )
2g
υ
υ
(υ )
Datum
x
2g 2g
υ (υ )
z =
z
z
υ =
(υ )
2g
(υ )
Total energy line
υ
x
(υ )υ =
υ υ
2g
o x
2
o x 2
x o x
z
o
2 2
xo
max
o z
o
xo
o
2
Fig. 4.10
Therefore,
=+
g
V
z
2
2
Constant
The total energy line is shown to be horizontal and at a distance of V2
/2g above
trajectory. The velocity at any point of the jet may be determined from its components Vx and
Vy. Thus V equals (Vx
2
+ Vy
2
) 1/2
. Here basic equations of projectile motion in physics are
used to determine the velocity components at any point along the trajectory:
( )
( ) gtVV
VV
zoz
xx
−=
= 0
The coordinates of the trajectory are expressed as follows:
( )
( ) 2
0
0
2
1
gttVz
tVx
z
x
−=
=
Where t is the elapsed after the liquid jet leaves the nozzle.
EXAMPLE 4.4: Water is discharged from a 5 cm (diameter) nozzle, which is inclined
at a 300
angle above the horizontal. If the jet strikes the ground at a horizontal distance of 5 m
and a vertical distance of 1 m from the nozzle as shown in Fig. 4.11, what is the discharge in
cubic meter per second?

5 m
1 m
30°
Fig. 4.11
SOLUTION:
( )
( ) jjzO
jjxO
VSinVV
VCosVV
5.030
866.030
0
0
==
==
Therefore the two coordinate equations for the trajectory are
( )
( ) 20
0
2
1
30
30
gttSinVz
tCosVx
j
j
−=
=
By eliminating t and solving for Vj from these two equations,
( )
( )
sec31.9
1577.052
81.9
866.0
5
30230
21
21
00
mV
zxTan
g
Cos
x
V
j
j
=
⎥
⎦
⎤
⎢
⎣
⎡
−×
=
⎥
⎦
⎤
⎢
⎣
⎡
−
=
Hence
sec0183.031.905.0
4
32
mVAQ jj =××==
π
4.6.3. Venturimeter
If the flow constriction in a pipe, as shown in Fig. 4.12, is well streamlined, the loss of
energy is practically equal to zero. The difference in velocity heads, Δ(V2
/2g), at two sections
across the constriction results in a change in potential heads, Δhpz=Δ(p/γ)+Δz. Such a device is
used for metering the quantity of flow Q in the pipe system by measuring the difference in
potential head.

Total energy line
z
z
P
γ
2
1P
γ
1
V
2g
2
1
V
2g
2
2
(h pz)2
(h pz)1
Datum
Pressure
line
2
1
2
Fig. 4.12
The Bernoulli’s equation for the two sections is
g
V
z
p
g
V
z
p
22
2
2
2
2
2
1
1
1
++=++
γγ
and the continuity equation is
2211 VAVAQ ==
These two equations may be solved for V1 and V2 it the two potential heads (hpz)
1=(p1/γ)+z1 and (hpz) 2=(p2/γ)+z2 are known. Hence, Q may be calculated. The difference in
potential heads may be measured either by means of two piezometric columns at two sections
or by using a differential manometer connected to the two sections.
EXAMPLE 4.5: The inclined Venturimeter shown in Fig. 4.13 is installed in a 20 cm
(diameter) water pipe line and has a throat diameter of 10 cm. Water flows in the upward
direction. For a manometer reading of 25 cm of mercury, what is the discharge in cubic meter
per second? The specific weight of mercury is 13.6 gr/cm3
.
SOLUTION: Denote h as the vertical distance between the throat and the water-
mercury interface in the manometer tube and y as the vertical distance between the centers of
the two sections in which manometer tappings are located. If the friction loss of flow through
the Venturimeter is neglected, Bernoulli’s equation can be applied to sections A and t:

W
ater
flow
25 cm
A
t
20 cm
10 cm
y
Mercury , γ = 13.6 gr/cm3
Fig. 4.13
g
V
z
P
g
V
z
p t
t
w
tA
A
w
A
22
22
++=++
γγ
By taking section A as the elevation datum,
g
V
y
P
g
Vp t
w
tA
w
A
22
0
22
++=++
γγ
(a)
The difference in pressure head (pA/γw – pt/γw) is determined by writing pressure
equation for the differential manometer starting at section A:
( )
w
t
w
A p
hyh
p
γγ
=−×−+−+ 6.1325.025.0
From this
25.06.1325.0 −×+=− y
pp
w
t
w
A
γγ
Which now is substituted into Equ. (a) to obtain,
m
g
V
g
V At
15.325.06.1325.0
22
22
=−×=− (b)

The continuity equation of flow is
tA
tA
ttAA
VV
VV
VAVA
4
1
1.0
4
2.0
4
22
=
××=××
=
ππ
Then, by substituting Vt/4 for VA in Equ. (b),
15.3
16
1
1
2
2
=⎟
⎠
⎞
⎜
⎝
⎛
−
g
Vt
Hence the velocity at the throat
sec12.8
15
1615.32
m
g
Vt =
××
=
The discharge is
sec064.012.810.0
4
32
mVAQ tt =××==
π
4.6.4. Stagnation Tube
A stagnation tube, such as the one shown in Fig. 4.14, is simply a bent tube with its
opening pointed upstream toward the approaching flow. The tip of the stagnation tube is
stagnation point, and stagnation tube, therefore measures the stagnation pressure (or the total
pressure), which is the sum of static pressure and the dynamic pressure.
s-stagnation point
υ = 0s
P
γ
1
υ1
P
γ
s
2g
υ2
1
Fig. 4.14

By using the Bernoulli equation and taking the stagnation point s be section 2 as
datum, the stagnation pressure ps is determined:
0
2
2
11
+=+
γγ
sp
g
Vp
or
2
11
2
1
Vpps ρ+= (4.11)
Stagnation = Static + Dynamic
pressure pressure pressure
4.6.5. Pitot Tube
A typical Pitot tube is shown schematically in Fig. 4.15. It consists of a stagnation
tube surrounded by a closed outer (static pressure) tube with annular space in between them.
Small holes are drilled through the outer tube to measure the static pressure. The stagnation
tube in the center measures the stagnation (total) pressure which is the sum of the static and
the dynamic pressure.
p
υ = 0
s
s
h =
γ υ
γ − γ 2gg
γ
γg
p1
υ1
1
υ
γ
1
2
Fig. 4.15
When the two tubes are connected to a differential pressure-measuring device, the
resulting difference in the pressure, ps-p1, is a direct measure of the velocity V1:
( )
ρ
1
1
2 pp
V s −
= (4.12)
EXAMPLE 4.6: The Pitot tube in Fig. 4.16 is carefully aligned with an air stream of
specific weight 1.23 kg/m3
. If the attached differential manometer shows a reading of 150 mm
of water, what is the velocity of the air stream?

Pitot tube
150 mm
Water
Air
p , Voo
Fig. 4.16
SOLUTION: Stagnation pressure will be found at the tip of the Pitot tube. Assuming
that the holes in the barrel of the static tube will collect the static pressure p0 in the
undisturbed air stream, the manometer will measure (ps-p0). Applying Equ. (4.11),
2
00
2
1
Vpps ρ+=
Therefore,
( )
sec90.48
81.9
00123.0
2
1
00123.0115.0
0
2
0
mV
V
=
××=−
4.6.6. Flow Over a Weir
The Bernoulli principle may be applied to problems of open flow such as the overflow
structure of Fig. 4.17. Such problems feature a moving liquid surface in contact with the
atmosphere and flow pictures dominated by gravitational action. A short distance upstream
from the structure, the streamlines will be straight and parallel and the velocity distribution
will be uniform.
1V
1
y
1
2
1V
2g
2V
αDatum
2
E.L.
x
α p = γx cos α
= x cos α
P
γ
V1
1V
V1
1V
V
2g
2
2
Fig. 4.17

In this region the quantity z+p/γ will be constant, the pressure distribution hydrostatic,
and the hydraulic grade (piezometric) line (for all stream tube) located in the liquid surface;
the energy line will be horizontal and located V1
2
/2g above the liquid surface. With
atmospheric pressure on the liquid surface the stream tube in the liquid surface behaves as a
free jet allowing all surface velocities to be computed from the positions of liquid surface and
energy line. The prediction of velocities elsewhere in the flow field where stream tubes are
severely convergent or curved is outside the province of one-dimensional flow. At section 2,
however (if the streamlines there are assumed straight and parallel), the pressures and
velocities may be computed from the one-dimensional assumption.
EXAMPLE 4.7: Refer to Fig. 4.17. At section 2 the water surface is at elevation 30.5
m, and the 600
spillway surface at elevation 30 m. The velocity in the water surface VS2 at
section 2 is 6.1 m/sec. Calculate the pressure and velocity on the spillway face at section 2. If
the bottom of the approach channel is at elevation 29 m, calculate the depth and velocity in
the approach channel.
SOLUTION:
Thickness of sheet of water at section 2 = m
Cos
1
60
305.30
0
=
−
Pressure on spillway face at section 2 = 20
5.06011 mtCos××
Elevation of energy line = m
g
40.32
2
1.6
5.30
2
=+
sec1.6
0.3
21
5.0
4.32
2
2
2
mV
g
V
F
F
=
++=
Which is to be expected from the one-dimensional assumption. Evidently all velocities
through section 2 are 6.1 m/sec, so
sec1.61.611 3
mq =××= per meter of spillway length
At section 1,
γ
1
11 0.29
p
zy +=+
and applying the Bernoulli equation,
m
yg
y
g
V
y 4.3
1.6
2
1
2
2
1
1
2
1
1 =⎟⎟
⎠
⎞
⎜⎜
⎝
⎛
×⎟⎟
⎠
⎞
⎜⎜
⎝
⎛
+=+

Solving this cubic equation by trial and error, the roots are y1 = 3.22 m, 0.85 m and -
0.69 m. Obviously the second and third roots are invalid here, so depth in approach channel
will be 3.22 m. The velocity V1 may be computed from
m
g
V
22.022.340.3
2
2
1
=−=
or from
22.3
10.6
1 =V
Both of which give V1 = 1.9 m/sec.
4.1.6. The Power of a Stream of Fluid
A stream of fluid could do work as a result of its pressure p, velocity V and elevation z
and that the total energy per unit weight H of the fluid is given by
z
g
Vp
H ++=
2
2
γ
If the weight per unit time of fluid is known, the power of the stream can be
calculated, since
Power = Energy Per unit time = (Weight/Unit time)×(Energy/Unit weight)
If Q is the volume rate (discharge) of flow,
Weight per unit time gQQ ργ ==
Power ⎟⎟
⎠
⎞
⎜⎜
⎝
⎛
++== z
g
Vp
gHgQH
2
2
γ
ρρ
Power gQzQVpQ ρρ ++= 2
2
1
(4.13)
EXAMPLE 4.8: Water is drawn from a reservoir, in which the water level is 240 m
above datum, at the rate of 0.13 m3
/sec. The outlet of the pipeline is at datum level and is
fitted with a nozzle to produce a high-speed jet to drive a turbine of the Pelton wheel type. If
the velocity of the is 66 m/sec, calculate
a) The power of the jet,
b) The power supplied from the reservoir,
c) The head used to overcome losses,
d) The efficiency of the pipeline and nozzle in transmitting power.

SOLUTION:
a) The jet issuing from the nozzle will be at atmospheric pressure and at datum level so
that, in Equ. (4.13), p = 0 and z = 0. Therefore,
Power of jet = QV 2
2
1
ρ
KWW
kgm
14.28328314081.928862
sec2886213.066
81.9
1000
2
1 2
==×=
=×××=
b) At the reservoir, the pressure is atmospheric and the velocity of the free surface is zero
so that, in Equ. (4.13), p = 0, V = 0. Therefore,
Power supplied from reservoir = QzQgz γρ =
KWW
kgm
72.30630607281.931200
sec3120024013.01000
==×=
=××=
c) If, H1 = Total head at the reservoir, H2 = Total head at the jet, h = Head lost in
transmission,
Power supplied from reservoir = sec312001 kgmQH =γ
Power of issuing jet = sec288622 kgmQH =γ
Power lost in transmission = sec2338kgmQh =γ
Head lost in pipe = h = (Power lost)/(γQ)
mh 98.17
13.01000
2338
=
×
=
d) Efficiency of transmission = (Power of jet)/(Power supplied by reservoir)
Efficiency of transmission = %5.92925.0
31200
28862
==

4.7. IMPULSE-MOMENTUM EQUATION: CONSERVATION OF
MOMENTUM
The impulse-momentum equation for fluid flow can be derived from the well-known
Newton’s second law of motion. The resultant force F
r
acting on a mass particle m is equal to
the time rate of change of linear momentum of the particle:
( )
dt
Vmd
F
r
r
=
This law applies equally well to a system of mass particles. The internal forces
between any two mass particles of the system exists in pairs. They are both equal and
opposite of each other and, therefore, will cancel out as set forth in Newton’s third law of
motion. The external forces acting on mass particles of the system can then be summed up
and equated to the time of change of the linear momentum of the whole system,
( )
∑
∑=
dt
Vmd
F
r
r
(4.13)
If we define momentum by VmI
rr
= , then
∑
∑=
dt
Id
F
r
r
(4.14)
Extending Newton’s second law of motion to fluid flow problem, take as a free body
the fluid mass included between sections 1-1 and 2-2 within a length of a flow channel (Fig.
4.18).
dA2
2
2
θ2
2'
2'
υ
dt
2
1
1
1'
1'θ2
dA1
υ dt1
x
x
Stream tube
For a steady flow there is no
change in momentum during
dt for the fluid mass between
1`-1` and 2-2.
-ρQV1
ΣF
ρQV2
Fig. 4.18

The fluid mass of the free body 1-1 and 2-2 at time t1 moves to a new position 1’-1’
and 2’-2’ at time t2 when t2-t1 equals to dt. Sections 1’-1’ and 2’-2’ are curved because the
velocities of flow at these sections are non-uniform. It should be noted that, for steady flow,
the following continuity equation holds.
[Fluid mass within section 1-1 and 1’-1’] = [Fluid mass within section 2-2 and 2’-2’]
( ) ( )22221111 ′′=′′ MM
The momentum of the system at time t,
( ) ( )ttt III 12211111 ′′+′′=
rrr
( tt IudtdAuI 1221111
′′+= )
rrr
ρ (4.15)
The momentum of the system at time t+dt,
( ) ( ) dttdttdtt III +++
′′+′′= 22221221
rrr
( ) 2221221 udtdAuII dttdtt
rrr
ρ+′′= ++ (4.16)
Change of momentum at dt time,
tdtt IIId
rrr
−= + (4.17)
Furthermore, when the flow is steady,
( ) ( ) dttt II +
′′=′′ 12211221
rr
From Eqs. (4.15) and (4.16),
111222 udtdAuudtdAuId
rrr
ρρ −=
or
111222 udAuudAu
dt
Id rr
r
ρρ −= (4.18)
From Eqs. (4.14) and (4.18),
∑ −= 111222 udAuudAuF
rrr
ρρ (4.19)
This equation is known as impulse-momentum equation.

If, however, average velocities V1 and V2 at sections 1-1 and 2-2 may be determined,
the impulse-momentum equation may be written,
∑ −= 111222 VdAVVdAVF
rrr
ρρ (4.20)
By taking integral over the areas,
∫∫∫∑ −=
12
111222
AA
dAVVdAVVF
rrr
ρρ
111222 VAVVAVK
rrr
ρρ −= (4.21a)
Here, ∫∑= FK
rr
is the total of the external forces acting on the control volume.
For a steady flow of an incompressible fluid, the impulse-momentum equation for
fluid flow may be simplified to the following form by first applying the continuity principle,
that is, Q = A1V1 = A2V2, to the flow system:
( )12 VVQK
rrr
−= ρ (4.21b)
If we take the velocity components for x and y-axes, Equ. (4.21b) takes the form of,
( )
( yyy
xxx
VVQK
VVQK
12
12
−=
−=
ρ )
ρ
(4.22)
These components can be combined to give the resultant force,
22
yx KKK +=
r
(4.23)
If D’Alembert’s principle is applied to the flow system, the system is brought into
relative equilibrium with the inclusion of inertia forces. The value of K is positive in the
direction if V is assumed to be positive.
For any control volume, the total force K that acts upon it in a given direction will be
made up of three component forces:
=1K
r
Force exerted in the given direction on the fluid in the control volume by any
solid body within the control volume or coinciding with the boundaries of the control volume.
=2K
r
Force exerted in the given direction on the fluid in the control volume by body
forces such as gravity. (Weight of the control volume).
=3K
r
Force exerted in the given direction on the fluid in the control volume by the
fluid outside the control volume. (Pressure forces, always gage pressures were taken).

=1VQ
r
ρ Rate of change of momentum in the direction of 1V
r
.
=2VQ
r
ρ Rate of change of momentum in the opposite direction of .2V
r
Thus,
( )12321 VVQKKKK
rrrrrr
−=++= ρ (4.24)
The force F exerted by the fluid on the solid body inside or coinciding with the control
volume in the given direction will be equal and opposite to 1K
r
so that . The
directions of the forces acting on a control volume can be shown schematically in Fig. (4.19).
1KF
rr
−=
ρQV
1
1
2
ρQV
2
K
2
1
Fig. 4.19
4.7.1. Momentum Correction Factor
The momentum equation (4.24) is based on the assumption that the velocity is
constant across any given cross-section. When a real fluid flows past a solid boundary, shear
stresses are developed and the velocity is no longer uniform over the cross-section. In a pipe,
for example, the velocity will vary from zero at the wall to a maximum at the center. Then,
Equ. (4.24) takes the form of,
( )1122 VVQK
rrr
ββρ −=
Dimensionless momentum correction factor β accounts for the non-uniform
distribution of velocity across the flow section. Obviously,
∫=
A
dAv
AV
2
2
1
β (4.26)
and the numerical value of β is always greater one. In problems of turbulent flow in pipes, β
is approximately equal to one.
Thus, Equ. (4.25) takes the form of Equ. (4.24) for the most practical problems of
turbulent flow.
( )12 VVQK
rrr
−= ρ (4.24)

4.7.2. Application of the Impulse-Momentum Equation
The impulse-momentum equation, together with the energy equation, and the
continuity equation, furnishes the basic mathematical relationships for solving various
engineering problems in fluid mechanics. In contrast to the energy equation, which is a scalar
equation, each term in the impulse-momentum equation represents a vector quantity. The
energy equation describes the conservation of energy and the average changes in the energies
of flow along a flow passage, whereas the impulse-momentum equation relates the over-all
forces on the boundaries of a chosen region in a flow channel without regard to the internal
flow phenomenon. In many instances, however, both the impulse-momentum equation and
the energy equation are complementary to each other.
Since the impulse-momentum equation relates the resultant external forces on a
chosen free body of fluid in a flow channel to the change of momentum flux at the two end
sections, it is especially valuable in solving those problems in fluid mechanics in which
detailed information on the flow process may be either lacking or rather difficult to evaluate.
In general, the impulse-momentum equation is used to solve the following two types of flow
problems.
1) To determine the resultant forces exerted on the boundaries of a flow passage by
a stream of flow as the flow changes its direction or its magnitude of velocity or
both. Problems of this type include pipe bends and reducers, stationary and
moving vanes, and jet propulsion. In such cases, although the fluid pressures on
the boundaries may be determined by means of the energy equation, the resultant
forces on the boundaries must be determined by integrating the pressure forces.
2) To determine the flow characteristics of non-uniform flows in which an abrupt
change of flow section occurs. Problems of this type, such as a sudden
enlargement in a pipe system or a hydraulic jump in an open-channel flow,
cannot be solved by using the energy equation alone, because there is usually an
unknown quantity of energy loss involved in each of these flow processes. The
impulse-momentum equation must be used first to determine the flow
characteristics. Then the energy equation may be used to evaluate the amount of
energy loss in the flow process.
4.7.1.1. Force Exerted by a Flowing Fluid on a Contracting Pipe on a Horizontal
Plane
The change of momentum of a fluid flowing through a pipe bend induces a force on
the pipe. Consider the pipe bend shown in Fig. 4.20.
α
Fy
Fx
F
V 2
A 2
V 11
A 1
y
x
Fig. 4.20

The fluid enters the bend with velocity V1 through area A1 and leaves with a velocity
V2 through area A2 after having been turned through an angle α. Let F be the force required to
hold the pipe in equilibrium against the pressure of the fluid. Fx and Fy are the component
forces in the negative x and y directions, respectively. Equ. (4.24) can now be employed to
determine the magnitude of the force F. Along the x-direction we have,
( ) ααρ CosApApFVCosVQ x 221112 −+−=− (a)
and in the y-direction we have,
( ) ααρ SinApFSinVQ y 222 0 +−=+− (b)
Then the total force is given by,
( )
( )[ ] }⎪⎩
⎪
⎨
⎧
+−++
−++−+
=+= 21
1212122221112121
2
2
2
2
2
1
2
121
2
2
2
1
22
22
22
2
αρα
αρ
CosAVpAVpAVpAVpQCosAApp
ApApCosVVVVQ
FFF yx
(c)
But, from the continuity equation the velocities are related by,
1
2
1
2 V
A
A
V =
Thus, Equ. (c) becomes,
21
1
2
1
2
2
1
2
2
1
22
1
2
1
1
2
2
2
1
121
2
2
2
2
1
2
1222
21
221
⎪
⎪
⎪
⎭
⎪⎪
⎪
⎬
⎫
⎪
⎪
⎪
⎩
⎪⎪
⎪
⎨
⎧
⎥
⎥
⎦
⎤
⎢
⎢
⎣
⎡
⎟⎟
⎠
⎞
⎜⎜
⎝
⎛
⎟⎟
⎠
⎞
⎜⎜
⎝
⎛
−⎟⎟
⎠
⎞
⎜⎜
⎝
⎛
⎟⎟
⎠
⎞
⎜⎜
⎝
⎛
++
⎥
⎦
⎤
⎢
⎣
⎡
⎟⎟
⎠
⎞
⎜⎜
⎝
⎛
+−++⎟⎟
⎠
⎞
⎜⎜
⎝
⎛
+−
=
α
αραρ
Cos
A
A
p
p
A
A
p
p
Ap
Cos
A
A
p
A
A
pppQ
A
A
Cos
A
A
VQ
F (d)
For equal areas (A1 = A2), Equ. (d) reduces to,
( )( )
21
1
2
2
1
22
1
2
121
2
1
2
2112
⎪⎭
⎪
⎬
⎫
⎪⎩
⎪
⎨
⎧
⎥
⎥
⎦
⎤
⎢
⎢
⎣
⎡
⎟⎟
⎠
⎞
⎜⎜
⎝
⎛
−⎟⎟
⎠
⎞
⎜⎜
⎝
⎛
++++−= αραρ Cos
p
p
p
p
ApppVCosQF
and, if the bend is 900
, the force for the constant area bend becomes,
( )
21
2
2
12
1
2
121
2
1
2
12
⎪⎭
⎪
⎬
⎫
⎪⎩
⎪
⎨
⎧
⎥
⎥
⎦
⎤
⎢
⎢
⎣
⎡
⎟⎟
⎠
⎞
⎜⎜
⎝
⎛
−++++=
p
p
ApppVQF ρρ

EXAMPLE 4.8: When 300 lt/sec of water flow through this vertical 300 mm by 200
mm pipe bend, the pressure at the entrance is 7 t/m2
. Calculate the force by the fluid on the
bend if the volume of the bend is 0.085 m3
.
F2
1
60°
1.5 m
0.6 m
2
NF1
60°
r
0.525m
V = 9.55 m/s2 z
Fz F
W
θ
Fx
x1V = 4.24 m/s
Fig. 4.21
SOLUTION: From the continuity principle,
sec55.9
2.0
3.044
sec24.4
3.0
3.044
22
2
2
22
1
1
2211
m
D
Q
V
m
D
Q
V
AVAVQ
=
×
×
==
=
×
×
==
==
ππ
ππ
and from the Bernoulli equation,
62.19
55.9
5.1
62.19
24.4
07
22
2
2
2
2
2
2
2
2
1
1
1
++=++
++=++
γ
γγ
p
g
V
z
p
g
V
z
p
m
p
77.12
=
γ
, 2
2 77.1 mtp =
Now, for the free-body diagram, the pressure forces F1 and F2 may be computed,
tonF
tonF
056.077.12.0
4
495.073.0
4
2
2
2
1
=××=
=××=
π
π

With this and velocity diagram,
0=∑x
tonF
CosF
CosQVCosFQVFF
x
x
x
799.0
6055.93.0
81.9
1
056.024.430.0
81.9
1
495.0
6060
0
2
2
0
211
=
⎟
⎠
⎞
⎜
⎝
⎛
××++××+=
+++= ρρ
0=∑z
( )
tonF
SinF
SinQVFF
z
z
z
386.0
085.016055.930.0
81.9
1
056.0
085.060
0
0
22
=
×+⎟
⎠
⎞
⎜
⎝
⎛
××+=
×++= γρ
tonFFF zx 869.0386.0779.0 2222
=+=+=
483.0
799.0
386.0
===
x
z
F
F
Tanθ , 0
8.25=θ
The plus signs confirm the direction assumptions for Fx and Fz. Therefore the force on
the bend is 0.87 ton downward to the right at 25.80
with horizontal.
Now, assuming that the bend is such shape that the centroid of the fluid therein is
0.525 m to the right of section 1 and that F1 and F2 act at the centroids of sections 1 and 2,
respectively. We take moments about the center of section 1 to find the location of F,
81.9
1
30.06055.96.0
81.9
1
30.06055.95.1
60056.06.060056.05.1085.0525.087.0
00
00
××××−××××−
=××+××+×+×−
SinCos
SinCosr
mr 56.0=
4.7.1.2. Reaction of a Jet
In Chapter (4.6.1) Torricelli’s theorem for the efflux velocity from an orifice in a large
tank was derived. The momentum theorem can now be applied to this example to determine
the propulsive force created by the orifice flow. In Fig. 4.22 is shown a large tank with its
surface open to the atmosphere and with an orifice area A2.
We assume that A2<<A1. Then the velocity of the jet by Equ. (4.10),
ghV 22 =
and
22VAQ =

A2
2P
V22
0P
F h
Fig. 4.22
Let F represent the force necessary to hold the tank in equilibrium. Then Equ. (4.22)
becomes,
( )02 −= VQF ρ
Therefore, the propulsive force or thrust induced by the jet is given by,
2QVFT ρ−=−=
EXAMPLE 4.9: A jet of water of diameter d = 50 mm issues from a hole in the
vertical side of an open tank which is kept filled with water to a height of 1.5 m above the
center of the hole (Fig. 4.23). Calculate the reaction of the jet on the tank and its contents, a)
When it is stationary, b) When it is moving with a velocity u = 1.2 m/sec in the opposite
direction to the jet relative to the tank remains unchanged. In the latter case, what would be
the work done per second?
1.5 m
Contol volume
V
Jet diameter 50 mm
u
Fig. 4.23
SOLUTION: Take the control volume shown in Fig. 4.23. In Equ. (4.24), the
direction under consideration will be that of the issuing jet, which will be considered as
positive in the direction of the jet; therefore, K2 = 0, and, if the jet is assumed to be at the
same pressure as the outside of the tank, K3 = 0. Force exerted by fluid system in the direction
of motion,
( 121 VVQKR −−=−= )ρ (a)
The velocity of the jet may be found by applying Torricelli’s equation (Equ. 4.10),
sec42.55.181.9222 mghV =××==

Mass discharge per unit time,
mkgM
V
d
QM
sec085.1
42.5
4
05.0
81.9
1000
4
2
2
2
=
×
×
×===
ππ
ρρ
a) If the tank is stationary,
V2 = 5.42 m/sec
V1 = Velocity at the free surface = 0
Substituting in Equ. (a), reaction of jet on the tank,
kgMVQVR 88.542.5085.122 =×=== ρ
b) If the tank is moving with a velocity u in the opposite direction to the of the jet, the
effect is to superimpose a velocity of (–u) on the whole system:
uVV −=
′
22 , uV −=1
Thus,
212 VVV =−
Thus, the reaction of the jet R remains unaltered at 5.88 kg.
Work done per second = Reaction × Velocity of the tank
WattkgmuRW 22.69sec056.72.188.5 ==×=×=
4.7.1.3.Pressure Exerted on a Plate by a Free Jet
Consider a jet of fluid directed at the inclined plate shown in Fig. 4.24. Suppose we
are interested in equilibrium against the pressure of the jet.
F
2
1
V1 Q1
V2
Q2
α
0V
0Q
Fig. 4.24

For a free jet the static pressure is the same for all points in the jet. Thus the velocities
can be related by,
210 VVV == (a)
In addition, for an inviscid fluid there can be no shearing force parallel to the plate
surface; thus, the reaction force is normal to the plate surface. From the momentum theorem
this force must be equal to the rate of momentum change normal to the plate surface. For this
case,
αρ SinQVF 00= (b)
where Q0 = V0A and A is the cross-sectional area of the jet. It is interesting to note that the
division of flow along the plate is uneven. The magnitudes of the flow rates along the plate
can be determined by a consideration of the momentum theorem parallel to the plate. In this
case,
( ) 0002211 =−− αρρρ CosVQVQVQ (c )
Also, the continuity equation stipulates that,
210 QQQ += (d)
Combination of Eqs. (a), (c), and (d) leads to the following results for discharges:
( αCos
Q
Q += 1
2
0
1 ) (e)
( αCos
Q
Q −= 1
2
0
2 ) (f)
EXAMPLE 4.10:
Calculate the force exerted by a jet of water 20 mm in diameter which strikes a flat
plate at an angle of 300
to the normal of the plate with a velocity of 10 m/sec if, a) The plate is
stationary, b) The plate is moving in the direction of the jet with a velocity of 2 m/sec.
SOLUTION:
a) The angle α shown in Fig. 4.24 is 900
-300
=600
; hence the normal force [Equ.(b)] is,
kgSinF 77..2601010
4
02.0
81.9
1000 0
2
=×××
×
×=
π

b) The change of velocity on impact in this case is,
sec80 mVV p =−
The normal force is,
kgSinF 77.16088
4
02.0
81.9
1000 0
2
=×××
×
×=
π
4.7.1.4. Stationary and Moving Vanes: The Impulse Turbine
Fig. 4.25 shows a free jet, which is deflected by a stationary curved vane through an
angle α. Here the jet is assumed to impinge on the vane tangentially. Hence, there is no loss
of energy because of impact. Since the friction loss of the flow passing along the smooth
surface of the stationary vane is almost equal to zero, the magnitude of the jet velocity
remains unchanged as it flows along the vane if the small difference in elevation between the
two ends of the vane is neglected as was shown in [Equ. (c). Pressure exerted on a plate by a
free jet].
Fy
Fx
F
V
V
F
Fx
Fy
ρQV
- ρQV
Stationary vane
α
Fig. 4.25
Therefore, the two components Fx and Fy of the F exerted by the stationary vane on the
jet of fluid may be determined from the following impulse-momentum equations:
0−=
−=−
αρ
ραρ
QVSinF
QVQVCosF
y
x
The force components, which exerts on the vane are equal and opposite to Fx and Fy
shown in Fig. 4.25.
Next, consider the moving vane in Fig. 4.26, which is moving with a velocity u in the
same direction as the approaching jet. The free jet of velocity V hits the moving vane
tangentially. This type of problem may be analyzed by applying the principle of relative
motion to the whole system.

θ
Fy
Fx
F
V = v - u
F
Fx
Fy
QρVe
- ρQV
i
v
u
u
u
Actual direction
of the jet when
the vane is moving
V
=
v-u
e
u
v
Fig. 4.26
This is done by bringing the moving vane in a stationary state before the entrance V
and the exit Ve must be relative velocities of the jet at these two sections with respect to vane.
The entrance velocity of the jet relative to the vane is Vi = V-u, and the magnitude of this
relative velocity remains the same along the curved surface of the vane if the friction loss is
assumed to be zero. Thus, Ve = V-u, and the direction of the exit velocity relative to the vane
is shown in Fig. 4.26. Therefore, the force components Fx and Fy exerted by the moving vane
on the jet are determined by applying the impulse-momentum equations to the flow system:
( ) ( )
( )( )
( ) 0
1
−−=
−−=
−⎟
⎠
⎞
⎜
⎝
⎛
−−=−
αρ
αρ
ραρ
SinuVQF
CosuVQF
uV
V
V
QCosuVQF
y
x
i
x
Again, the force components which jet exerts on the moving vane must be equal and opposite
to Fx and Fy shown in Fig. 4.26.
In mechanics the power developed by a working agent is defined as the rate at which
work done by that agent. When a jet of fluid strikes a single moving vane of Fig. 4.26, the
power developed is equal to Fx×u, or
Power = ( )( uCosuVQ )αρ −− 1
Force component Fy does not produce any power because there is no motion of the
vane in the y direction.
In the engineering application of the principle of moving vane to an impulse turbine
wheel (Fig. 4.27), a series of vanes is mounted on the periphery of a rotating wheel. The vanes
are usually spaced that the entire discharge Q is deflected by vanes.

( b )
V
V
( a )
Actual path
of the jet
V
Relative velocity of
the jet with respect
to the turbine vanes
U V
u
V
e
e
Fig. 4.27
Therefore, the total power output of a frictionless impulse turbine is,
( )( )uCosuVQPT αρ −−= 1 (4.25)
This equation indicates that, for any free jet of discharge Q and velocity V, the power
developed in an impulse turbine is seen to vary with both the deflection angle α of the vane
and the velocity u at which the vanes move. Mathematically, the values of α and u to produce
maximum turbine power for a given jet may be determined by taking partial derivatives
∂PT/∂α and ∂PT/∂u and then equating them zero. Thus,
( ) ( ) 01 =+−=
∂
∂
αρ
α
SinuuVQ
PT
and
0
180=α ; ( ) ( )uVQuPT −==
ρα 20
180
Also,
( )( ) 021 =−−=
∂
∂
uVCosQ
u
PT
αρ
and,
2
V
u = ; ( ) ( )
4
1
2
2
V
CosQP VuT αρ −==
The maximum turbine power is obtained when α=1800
and u=V/2.
Therefore,
( )
2
2
max
V
QPT ρ=

which is exactly the power in the free jet of fluid. In practice, however, the deflection angle of
the vanes on an impulse wheel is found to be about 170 degrees and the periphery speed of
the impulse wheel to be approximately u = 0.45V.
EXAMPLE 4.11: An impulse turbine of 1.8 m diameter is driven by a water jet of 50
mm diameter moving at 60 m/sec. Calculate the force on the blades and the power developed
at 250 r/min. The blade angles are 1500
.
SOLUTION: The velocity of the impulse wheel is,
sec6.239.02
60
250
mu =××= π
The flow rate is,
sec12.06005.0
4
32
mQ =××=
π
The working component of force on the fluid is,
( )( )
( )( )
kgF
CosF
CosuVQF
x
x
x
831
15016.236012.0
81.9
1000
1
0
=
−−××=
−−= αρ
The power developed,
WattkgmuFP x 192390sec196126.23831 ==×=×=
4.7.1.5. Sudden Enlargement in a Pipe System
There is a certain amount of energy lost when the fluid flows through a sudden
enlargement in a pipe system such as that shown in Fig. 4.28.
The continuity equation for the flow is,
22111 VAVAVAQ e ===
Since the velocity Ve of the submerged jet may be assumed to be equal to V1, by
reason of Bernoulli theorem, pe equals to p1. This latter condition is readily verified in the
laboratory.

V = Ve 1V1
2V
P
γ
1
V
2g
1
2
L
21 e
ρQV ρQV1 e
ρQV2
P21P = Pe
2V
2g
2
P
γ
2
h
Fig. 4.28
The impulse-momentum equation for the flow of fluid in the pipe between sections e
and 2 is,
( ) ( 1222 VVQAppe −=− )ρ
or
( )
⎥
⎥
⎦
⎤
⎢
⎢
⎣
⎡
−⎟⎟
⎠
⎞
⎜⎜
⎝
⎛
=−=
−
2
1
2
2
1
2
1
12
2
21
A
A
A
A
g
V
VV
gA
Qpp
γ
The energy equation may now be written between sections 1 and 2 in the following
form:
Lh
g
Vp
g
Vp
++=+
22
2
22
2
11
γγ
Solving these three equations simultaneously gives,
( )
2
2
1
2
1
2
21
1
22 ⎟⎟
⎠
⎞
⎜⎜
⎝
⎛
−=
−
=
A
A
g
V
g
VV
hL (4.26)
This is the well-known Borda-Carnot equation.

4.7.1.6. Hydraulic Jump in an Open Channel Flow
A hydraulic jump in an open channel flow is a local phenomenon in which the surface
of a rapidly flowing stream of liquid rises abruptly. This sudden rise in liquid surface is
accompanied by the formation of extremely turbulent rollers on the sloping surface in the
hydraulic jump as that shown in Fig. 4.29. An appreciable quantity of energy is dissipated in
this process when the initial kinetic energy of flow is partly transformed into potential energy.
( h )j
y
Total energy line
γ y1
( b )
2
Water
surface
γ by1
2 1
ρ QV
y 1V
1
1
ρ QV2
( a )
2
V
2g
1
γ y2
γ by1
2 2
2
2
V2
b
V / 2g1
L
2
y1
y2
Rollers
Fig. 4.29
The hydraulic jump shown in Fig. 4.29 is assumed to occur in a horizontal rectangular
channel of width b (perpendicular to the plane of paper). Because the flow is guided by a solid
boundary at the bottom of the channel, hydrostatic pressure distribution exists at both the
upstream section 1 and downstream section 2 from the hydraulic jump. The following two
assumptions are made in the mathematical analysis of a hydraulic jump: 1) The friction loss
of flow at the wetted surface of the channel between sections 1 and 2 is assumed to be
negligible; 2) The velocity distribution of flow at both sections is assumed to be uniform.
For steady flows the continuity equation yields,
2211 VbyVybQ == or 2211 VyVy =
and the impulse-momentum equation for the free body of the flow system (Fig.4.29b) is,
12
2
2
2
1
22
QVQV
byby
ρρ
γγ
−=−

or
2
11
2
22
2
2
2
1
22
VyVy
yy
ρρ
γγ
−=−
of the four quantities, V1, y1, V2, and y2, two must be given; the other two can be determined
by the simultaneous solution of these two equations.
After the flow characteristics are all determined, the loss of energy of flow in a
hydraulic jump can readily be evaluated by the application of the energy equation, that is,
⎟⎟
⎠
⎞
⎜⎜
⎝
⎛
+−⎟⎟
⎠
⎞
⎜⎜
⎝
⎛
+=
g
V
y
g
V
yhL
22
2
2
2
2
1
1 (4.27)
EXAMPLE 4.12: As shown in the Fig. 4.30, 10 m3
/sec of water per meter of width
flows down an overflow spillway onto a horizontal floor. The velocity of flow at the toe of the
spillway is 20 m/sec. Compute the downstream depth required at the end of the spillway floor
to cause a hydraulic jump to form and the horsepower dissipation from the flow in the jump
per meter of width.
L
1
V = 20 m/sec1
V2
q =
10 m /sec
m
3
V
2g
2
1
y2
2V
2g
2
Total energy
line
( h )j
Fig. 4.30
SOLUTION: The continuity equation of flow is,
221
3
20sec//10 yVymmq ===
Hence,
my 5.01 =
The momentum equation relating flow conditions at two end sections of the jump is,
22
22
2
2
2
205.0
81.9
1
81.9
1
2
1
2
5.01
××−××=
×
−
×
Vy
y

Solving these equations simultaneously yield,
sec63.12 mV = and my 14.62 =
From Equ. (4.27) the loss of energy of flow in the hydraulic jump is,
⎟⎟
⎠
⎞
⎜⎜
⎝
⎛
+−⎟⎟
⎠
⎞
⎜⎜
⎝
⎛
+=
gg
hL
2
63.1
14.6
2
20
5.0
22
mhL 60.14= per meter width
Horsepower dissipation Hp
QhL
1946
75
60.14101000
75
=
××
==
γ

BASIC EQUATIONS FOR ONE-DIMENSIONAL FLOW (Chapter 04)

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BASIC EQUATIONS FOR ONE-DIMENSIONAL FLOW (Chapter 04)