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ESDU 80025
Endorsed byThe Royal Aeronautical SocietyThe Institution of
Structural Engineers
Mean forces, pressures and flow fieldvelocities for circular
cylindrical
structures:single cylinder with two-dimensional flow
Issued October 1980With Amendments A to C
June 1986Supersedes ESDU 70013
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ESDU 80025ESDU DATA ITEMS
Data Items provide validated information in engineering design
and analysis for use by, or under the supervisionof, professionally
qualified engineers. The data are founded on an evaluation of all
the relevant information, bothpublished and unpublished, and are
invariably supported by original work of ESDU staff engineers or
consultants.The whole process is subject to independent review for
which crucial support is provided by industrial
companies,government research laboratories, universities and others
from around the world through the participation of someof their
leading experts on ESDU Technical Committees. This process ensures
that the results of much valuablework (theoretical, experimental
and operational), which may not be widely available or in a readily
usable form, canbe communicated concisely and accurately to the
engineering community.
We are constantly striving to develop new work and review data
already issued. Any comments arising out of youruse of our data, or
any suggestions for new topics or information that might lead to
improvements, will help us toprovide a better service.
THE PREPARATION OF THIS DATA ITEM
The work of on this particular Item was monitored and guided by
the Wind Engineering Panel which has the followingconstitution:
The Panel has benefited from the participation of members from
several engineering disciplines. In particular,Dr A.R. Flint has
been appointed to represent the interests of structural engineering
as the nominee of the Institutionof Structural Engineers.
(Continued on inside back cover)
ChairmanMr T.V. Lawson Bristol University
MembersMr K.C. Anthony Ove Arup and PartnersDr D.J. Cockrell
University of Leicester Prof. A.G. Davenport* University of Western
Ontario, CanadaDr A.R. Flint Flint and NeillMr D.H. Freeston*
* Corresponding Member
University of Auckland, New ZealandMr R.I. Harris Cranfield
Institute of TechnologyMr R.A. Lyons Atkins Research and
DevelopmentMr J.R. Mayne Building Research EstablishmentMr R.J.
Melling Post Office TelecommunicationsDr G.A. Mowatt CJB - Earl and
Wright LtdMr J.R.C. Pedersen IndependentMr D.J.W. Richards Central
Electricity Research LaboratoriesMr C. Scruton IndependentMr R.E.
Whitbread National Maritime Institute.
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.ESDU 80025MEAN FORCES, PRESSURES AND FLOW FIELD VELOCITIES FOR
CIRCULAR CYLINDRICAL STRUCTURES: SINGLE CYLINDER WITH
TWO-DIMENSIONAL FLOW
CONTENTS
Page
1. NOTATION AND UNITS 1
2. PURPOSE, SCOPE AND USE OF THIS DATA ITEM 32.1 Purpose 32.2
Scope 42.3 Use of the Data Item 42.4 Applicability, Limitations and
Uncertainties 5
3. DRAG COEFFICIENT OF ISOLATED CYLINDER NORMAL TO FLOW 53.1 The
Roughness Factor R 63.2 The Turbulence Factor T 73.3 Calculation
Procedure For Evaluating CD0 73.4 Wind-tunnel Simulation of High
Reynolds Number Flow 8
4. EFFECT OF CYLINDER INCLINATION TO FLOW 94.1 Subcritical
Reynolds Numbers Ree < 3 105 94.2 Supercritical Reynolds Numbers
(Ree > 3 105) 104.3 Curved Cylinders 11
5. CYLINDERS WITH SURFACE IRREGULARITIES 115.1 Stranded Cables
115.2 Perforated Cylinders and Shrouds 11
5.2.1 Derivation 125.3 Effect of Fins and Strakes 125.4 Effect
of Other Spanwise Protrusions 13
5.4.1 Comments on the effects of protrusions 14
6. PROXIMITY EFFECT OF PLANE SURFACE PARALLEL TO CYLINDER AXIS
15
7. MEAN AND FLUCTUATING PRESSURE DISTRIBUTIONS, VELOCITY FLOW
FIELD 177.1 Mean Pressure Distribution at Surface 17
7.1.1 Derivation of method for mean pressure distribution at
surface 187.2 Fluctuating Pressure Distribution at Surface 187.3
Velocity Flow Field Away From Surface 20
7.3.1 Derivation of velocity flow field parameters 20i
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.ESDU 800258. EXAMPLES 20
8.1 Example 1 208.2 Example 2 218.3 Calculation Sheet for
Examples (from Table 10.3) 238.4 Calculation Sheet for Example 1
(from Table 10.5) 24
9. REFERENCES AND DERIVATION 259.1 References 259.2 Derivation
25
10. TABLES 28
FIGURES 1 to 15 33 to 49
APPENDIX A GENERAL FEATURES OF THE FLOW AROUND A CIRCULAR
CYLINDER 51
A1. CYLINDER WITH TWO-DIMENSIONAL FLOW 51
A2. INFLUENCE OF FREE-STREAM TURBULENCE 52
A3. INFLUENCE OF SURFACE ROUGHNESS 53
APPENDIX B SURFACE ROUGHNESS CHARACTERISTICS 55
B1. EQUIVALENT SAND GRAIN ROUGHNESS 55
B2. ADDITIONAL REFERENCES 56
B3. TABLE OF EQUIVALENT ROUGHNESS VALUES FOR VARIOUS TYPES OF
SURFACE FINISH 56
APPENDIX C SUMMARY OF EQUATIONS FOR SOME OF THE GRAPHICAL DATA
57
C1. EQUATION FITS TO THE DATA 57
APPENDIX D RANGE OF EXPERIMENTAL DATA 60
D1. SOURCES AND RANGE OF DATA USED 60ii
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.ESDU 80025MEAN FORCES, PRESSURES AND FLOW FIELD VELOCITIES FOR
CIRCULAR CYLINDRICAL STRUCTURES: Single Cylinder with
Two-dimensional Flow
1. NOTATION AND UNITS
SI Unit
mean drag coefficient of two-dimensional circular cylinder whose
longitudinal axis is normal to flow; drag force per unit
set of force coefficients acting along and normal to flow
direction and to cylinder axes respectively (see Sketch 4.1); force
per unit
mean pressure coefficient at cylinder surface,
instantaneous value of the fluctuating pressure coefficient
extreme value of Cp(t)
value of Cp on cylinder surface in wake region (see Sketch
7.1)
minimum value of Cp on cylinder surface (see Sketch 7.1)
mean pressure coefficient at distance r from cylinder centre and
angle (see Sketch 7.2)
cylinder diameter m
protrusion height m
factor in Equation (4.7) accounting for effect of cylinder
inclination on CN
crest or peak factor (see Equation (7.9))
gap width between cylinder and plane surface (see Sketch 6.1)
m
intensities of turbulence; and (see Table 10.2 for typical
values)
length of cylinder m
lateral integral scale of u-component of turbulence (see Table
10.2 for typical values)
m
local static pressure N/m3
Reynolds number,
CD0length/ V2 D( )
CD ,CLCN ,CT
length/ V2 D( )
Cp p p( )/ V2( )Cp t( )
Cp t( )Cpb
Cpm
Cp r ,( )
D
d
f
g
h
Iu ,Iv u/V v/V
L
Lr u
p
Re VD /sec1
Issued October 1980With Amendments A to C, June 1986 60
pages
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.ESDU 80025critical Reynolds number, i.e. Re at which CD0 = 0.8
in rapid drag fall (see Appendix A)
effective Reynolds number, Re (see Section 3)
Re at which rapid fall in CD0 at transition begins (see Sketch
3.1)
distance between cylinder centre and point in flow field m
fluctuating components of free-stream velocity in direction of
flow, and normal to flow direction and cylinder longitudinal axis,
respectively
m/s
mean free-stream velocity m/s
local mean flow velocity at surface of cylinder m/s
local mean velocity in flow field at distance r from cylinder
centre and angle
m/s
effective mean free-stream velocity in boundary layer (see
Equation (6.1)) m/s
local mean free-stream velocity in boundary-layer flow (see
Sketch 6.1) m/s
length of plane surface upstream of cylinder location m
power-law index giving approximate variation of Vz with height
from surface
angle between local flow direction and free-stream direction
(see Sketch 7.2) deg
effective roughness height of surface (see Table 10.1 for
typical values) m
angular location of point (see Sketches 5.2, 7.1) deg
value of where Cp first equals Cpb deg
value of where Cp = Cpm deg
parameter defining effect of surface roughness on Ree (see
Section 3.1)
parameter defining effect of flow turbulence on Ree (see Section
3.2)
kinematic viscosity of free-stream m2/s
density of free-stream kg/m3
standard deviation of fluctuating pressure coefficient
standard deviations of u(t) and v(t) m/s
Recrit
Ree TRReD
Rex Vx/r
u t( ) v t( ),
V
Vs
V r ;( )
Veff
Vz
x
r ;( )b m RTCpu ,v2
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.ESDU 80025
2. PURPOSE, SCOPE AND USE OF THIS DATA ITEM
2.1 Purpose
The purpose of this Data Item is to provide data for estimating
the mean forces induced by flow around acylindrical structure of
circular cross-section. Only single cylinders are considered in
this Item; mean forceson cylinders in groups will be the subject of
a separate Data Item. In the present context the data applywhen the
effect of the flow around the free end (or ends) can be ignored
(e.g. for long cylinders).Reference 1 provides additional
information in the form of correction factors which can be applied
to thesedata to account for end effects and shear flow effects,
such as those associated with cantilever structures inthe
non-uniform atmospheric wind.
The circular cylinder is one of the most commonly occurring
shapes in engineering structures. Typicalexamples are chimney
stacks, towers, storage tanks, silos, cables, pipe lines, space
vehicles and missiles,and elements of structures such as lattice
towers and off-shore structures. Other examples are pipes andstruts
inside ducts but in these cases the confinement effects due to the
proximity of the duct walls must betaken into account (see ESDU
800249). In many situations the overall response (mean and
fluctuating) ofthe structure to the approaching flow, such as the
atmospheric wind, is needed for design purposes. ThisItem provides
data for estimating the mean components of loading. The fluctuating
components, such asthose arising from buffeting by a turbulent flow
or from vortex shedding, must also be considered;ESDU 870357
provides methods for estimating the maximum design loading due to
buffeting byatmospheric turbulence (along the wind direction) and
Reference 8 deals with the across-flow response dueto vortex
shedding.
angle between free-stream direction and normal to longitudinal
axis of cylinder (see Sketch 4.1)
deg
ratio of open area to total area
Subscripts
denotes value at critical Reynolds number
relates to effective value based on Veff
relates to value for gap width h
relates to value where Cp = Cpm
denotes maximum value
denotes value for cylinder inclined to flow at angle
denotes value for two-dimensional conditions (see Section
2.4)
denotes free-stream value
crit
eff
h
m
max
0
3
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.ESDU 800252.2 Scope
The data presented (used in conjunction with Reference 1 to
account for free-end effects and shear flow)form the basis for
estimating mean force coefficients acting on circular cylindrical
structures of many typesin a variety of conditions. The following
data can be obtained from this data Item.
It must be emphasised that with circular cylindrical structures
there are a number of parameters that canhave a very significant
effect on the flow-induced forces. The effects of the following
parameters areparticularly important and can be taken into account
when estimating data from this Item.
2.3 Use of the Data Item
To make the best use of this Data Item proceed as follows:
(i) Select the appropriate calculation sheet, or sheets, from
Tables 10.3 to 10.5. Read the generalbackground notes referred to
in the appropriate Sections of interest. (Section 8 contains two
workedexamples and Appendix A provides a general description of the
features of the flow around acircular cylinder.)
(ii) Take note of the general applicability and uncertainty of
the data (see Section 2.4).
(iii) If, for the structure under consideration, end effects are
significant (i.e. length to diameter ratio lessthan about 25 as
with most stacks and towers) and/or the approaching velocity
profile isnon-uniform, other correction factors must, in general,
be applied to the values obtained from thisItem; these correction
factors are given in Reference 1.
(iv) For repeated calculations many of the data in this Item can
be programmed using the equations inthe text and in Appendix C.
Data Section No.Drag coefficients of plain cylinders 3Force
coefficients of inclined cylinders 4Drag coefficients of stranded
cables 5.1Drag coefficients of perforated cylinders and perforated
shrouds 5.2Drag coefficients of cylinders with strakes 5.3Drag and
side force coefficients for cylinders with isolated spanwise
protrusions such as ribs, joints, icing droplets, cables and
pipes
5.4
Drag and side force coefficients of cylinder with its
longitudinal axis parallel to nearby plane surface
6
Mean pressure distributions 7.1Fluctuating pressure
distributions 7.2Velocity flow field around the cylinder 7.3
Parameter Section No.Reynolds number (up to full-scale values)
3,Roughness of cylinder surface (up to 3, 3.1Turbulence
characteristics of the approaching flow 3, 3.2Cylinder inclination
to flow direction (0 to 90) 4
/D 0.12 )=4
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.ESDU 800252.4 Applicability, Limitations and Uncertainties
The data presented in this Item are principally derived from
data associated with uniform, two-dimensionalflow conditions. This
means that either the cylinder is sufficiently long that end
effects, which induce athree dimensional flow around the tip, are
essentially localised to that region or that end effects
areminimised by placing the cylinder between end plates. In this
latter situation truly representativetwo-dimensional conditions
will only prevail if the length to diameter ratio of the cylinder
is greater thanabout 5 or 6; this then allows the three-dimensional
cell-like structure of the wake associated with vortexshedding to
develop naturally. Correction factors to account for finite-length
cylinders in shear (orboundary-layer) flow, such as the atmospheric
wind, are provided in Reference 1.
Other limitations on the use of the data are either implied by
the comments in the text and the Figures orby the range of
experimental data used to derive the various correlations
summarised in the Table inAppendix D. Where possible the data have
been interpolated and extrapolated to conditions other thanthose
for which experimental data are available.
The uncertainties of the data presented are, in general,
indicated on the appropriate Figures or discussed inthe related
text.
3. DRAG COEFFICIENT OF ISOLATED CYLINDER NORMAL TO FLOW
The calculation sheet in Table 10.3 provides a summary of the
steps required to estimate a value of CD0 fora given set of input
conditions. The following notes provide a background to the
derivation of the data.
The flow pattern around a circular cylinder (and the resulting
drag coefficient) are primarily determinedby the position of the
separation points at which the upstream boundary layer leaves the
cylinder surfaceto form the wake region. The location of the
separation points is primarily determined by the Reynoldsnumber and
turbulence characteristics of the approaching flow and by the
roughness of the cylinder surface.The flow pattern development from
very low to very high Reynolds numbers, and the general effects
ofturbulence and surface roughness, are described in Appendix A for
conditions where compressibility effectscan be ignored (Mach number
less than 0.25)*. In practice, the drag coefficient of a
two-dimensionalcircular cylinder can be correlated with flow and
surface roughness conditions in the form
as given by Figures 1a to 1c. The effective Reynolds number is a
modified Reynoldsnumber incorporating the factor , dependent on the
turbulence characteristics of the approaching flow,and dependent on
the surface roughness parameter .
The derivation of these factors is described in Sections 3.1 and
3.2 and their values for specified conditionsare given by Figures 2
and 3. The procedure for evaluating CD0 is described in Section
3.3, or the calculationsheet in Table 10.3 can be used for this
purpose. In addition Section 3.4 provides guidance on the use
ofthese effects to provide simulation of high Reynolds number flow
for wind-tunnel tests.
CD0 f Ree ,/D[ ]=
Ree TRRe=( )TR /D 5
* The effects of compressible flow around circular cylinders
such as axisymmetric bodies and stub cylinders normal or inclined
to the flowwill be considered in future Data Items to be included
in the Aerodynamics Sub-series.
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.ESDU 800253.1 The Roughness Factor R
Sketch 3.1 Effect of surface roughness
For the reasons summarised in Appendix A, increasing surface
roughness has the effect of decreasing thevalue of Re (= ReD) at
which the rapid fall in CD0 begins (see Sketch 3.1) and is a
parameter whichcharacterises this effect. It may be defined as the
ratio of Re for a smooth cylinder giving a specified valueof CD0 to
Re for a rough cylinder in the same free-stream giving the same
CD0, both measured in thetransition region following ReD ; in
practice it is related to . This relationship is shown in Figure
2which has been derived from an analysis of data for cylinders with
uniformly distributed roughness.However, Figure 2 (and Figure 1c.)
can be used for uniformly-distributed elements such as helical
strakestaking as the element height (usually about 0.1 D for a
helical strake).
Some approximate values of the quantity for a number of
different surfaces are given in Table 10.1.These values are
equivalent sand-grain roughness heights, the derivation of which is
discussed inAppendix B. Considerable variation in these values can
apply as indicated in Table 10.1. It is also importantto remember
that the deterioration of a surface with time usually increases the
surface roughness and, unlessspecial maintenance procedures are
employed, this should be taken into account when selecting
anappropriate value of .
CD0
Re1 log ReRe2
ReD
2
1
Moderately rough surface
Smooth surface/D 0.002 103
R = Re1/Re2
R
/D
6
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.ESDU 800253.2 The Turbulence Factor T
Turbulence in the approaching flow, such as the atmospheric
wind, has a strong effect on the variation ofCD0 with Re in the
transition region as illustrated in Sketch 3.2. The physical
reasons for this (and for therapid variation of CD0 with Re in the
transition region) are explained in Appendix A. An analysis of
datafrom various sources (see Appendix D) shows that the effect of
free-stream turbulence on CD0 becomesincreasingly important for Re
greater than about 104 although its effect decreases again for
(thevalue of Re at which CD0 begins to fall in the transition
region) and is negligible for . For agiven surface roughness this
effect is represented in Equation (3.1) by the factor . This
parameterdepends on Re and Recrit, which in turn is determined by
and , and is given by
. (3.1)
In general, Recrit is the value of Re at which CD0 falls to a
value of 0.8 in the transition region*. Figure 3aprovides values of
as a function of the turbulence parameter . The parameters and
represent the intensity and scale of the turbulence in the
approaching flow (Appendix A explains thephysical significance of
these properties) and typical values are given in Table 10.2.
3.3 Calculation Procedure For Evaluating CD0
(1) Obtain a value of the surface roughness parameter, , from
Table 10.1 and evaluate .
(2) Determine from Figure 2.
(3) Evaluate . If then the factor and steps 4 to 8 can be
ignored.
(4) Obtain typical values of the intensity (Iu) and scale of
turbulence from Table 10.2 and evaluate.
Sketch 3.2 Effect of turbulence in approaching flow
* Note that when is greater than about 8 103 then CD0 is always
greater than 0.8 but the definition of Recrit given by Equation
(3.1)
CD0
Recrit1Recrit 2
ReD
2 1
2
1
Turbulent free-stream(e.g. the atmospheric wind)
Free-stream with low turbulence(e.g. in a wind tunnel)
Subcritical Supercritical
Trans-critical
log Re
Re ReD>Re 3 106
TTcrit R
Recrit4.5 105TcritR---------------------=
/D
Tcrit Iu D/ Lr u( )1/5 IuLr u
/DR
Re VD/= Re 2 106> T 1.0Lr u( )
Iu D/ Lr
u( )1/57
must be used because it is compatible with the way in which the
method was derived. Typically, for a low-turbulence wing-tunnel
flow, is about 1.4 whereas for the atmospheric wing is about 10.
Tcrit Tcrit
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.ESDU 80025(5) Determine from Figure 3a.
(6) Evaluate .
(7) Evaluate Re/Recrit
(8) Determine from Figure 3b and hence evaluate .
(9) Evaluate .
(10) Determine CD0 from Figure 1a, 1b or 1c as appropriate.
3.4 Wind-tunnel Simulation of High Reynolds Number Flow
In wind-tunnel studies it is often difficult to simulate high
Reynolds number flow conditions associatedwith many full-scale
structures because of limitations on model size (and hence on Re).
In practice, thedata in Figures 1 to 3 show that the addition of
moderate surface roughness (and sometimes an increase inturbulence
in the approaching flow) can be used to promote supercritical flow
conditions at Reynoldsnumbers when the flow would otherwise have
been subcritical, as illustrated in Sketch 3.3. For
example,referring to Sketch 3.3, the pressure distribution
represented by conditions at A (relatively high Re,
relativelysmooth surface and low turbulence flow) is found to be
more or less identical to the pressure distributionrepresented by
conditions at B which relate to a rougher cylinder in turbulent
flow but at a significantlylower Re.
Sketch 3.3
This technique, however, has limitations. It cannot be used for
groups of cylinders since wake-interferenceeffects nullify the
Reynolds number equivalence. It cannot be used when Re is less that
about 3 104 sinceroughness then has no significant effect on the
flow regime. It can only be used sensibly over a relativelysmall
range of effective Reynolds numbers. However, the Data Item can be
used to provide guidance inascertaining the degree of additional
roughness (and turbulence) that would be required to generate
theappropriate supercritical flow conditions in a wind-tunnel
test.
TcritRecrit 4.5 10
5 / TcritR( )=
T 1( )/ Tcrit 1( ) TRee TRRe=
CD0
log Re
Subcritical flow
Rough surface, turbulent flowSmooth surface, smooth flow
Supercritical flow
AB
B8
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.ESDU 800254. EFFECT OF CYLINDER INCLINATION TO FLOW
A number of structures, or their components, are naturally
inclined to the approaching flow. Examples areleg members of
lattice structures and off-shore structures, bridge cables and pipe
lines. The data presentedin this Section provide force coefficients
giving either the drag force or the force normal to the cylinder
axis.
The method of allowing for cylinder inclination depends on
whether the flow is subcritical or supercritical . For subcritical
flow the simple cross-flow theory given in Section 4.1applies. For
supercritical flow the evidence is that this simple cross-flow
theory underestimates orCN for relatively smooth two-dimensional
cylinders and should not be used; Section 4.2 provides guidancefor
this situation.
The critical flow velocity (corresponding to Recrit) for an
inclined cylinder is found to be lower than thatfor the same
cylinder normal to the flow. In practice the critical Reynolds
number is approximatelyindependent of if expressed in terms of the
streamwise components so that
(4.1)
and more generally
(4.2)
The general calculation procedure for dealing with inclined
cylinders is set down in the calculation sheetin Table 10.3 but
Sketch 4.2 illustrates how the different methods for the
subcritical and supercritical flowregions fit together.
4.1 Subcritical Reynolds Numbers Ree < 3 105
Sketch 4.1
For subcritical Reynolds numbers experimental data show that the
force coefficients are dependent on thecomponent of free-stream
velocity normal to the cylinder axis, i.e. on , and on the
streamwisecomponent of Reynolds number. Thus for inclined cylinders
the normal force is given by
(4.3)
where CD0 is obtained from Figure 1 for .
Ree 3 105( )
CD0
Recrit VD /sec[ ]crit 4.5 105 / TcritR( )= =
Ree TR VD /vsec( )=
VN
CL0
CD0
CN
CTV
VN V cos=
CN CD0 2cos=
Ree TR VD /sec( )=9
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.ESDU 80025An analysis of data11 shows that the axial force is
small but that its variation with can be represented by(for )
(4.4)
For long, smooth circular cylinders, k = 0.033 but for a rough
or uneven cylinder, such as a stranded cable,k = 0.045 is a more
reasonable estimate.
Drag and side forces parallel to, and normal to, the free-stream
direction respectively can be obtained froma simple resolution of
forces. Thus,
, (4.5)
. (4.6)
4.2 Supercritical Reynolds Numbers (Ree > 3 105)
For supercritical Reynolds numbers data15 indicate that the
simple cross-flow theory described inSection 4.1 tends to
underestimate CN for relatively smooth, inclined circular
cylindrical members. Thereason for this is that while for the
laminar boundary layer (and the associated pressuredistribution)
tends to depend only on the cross-flow velocity, when transition to
turbulent flow in theboundary layer has occurred the subsequent
development and separation of the boundarylayer are adversely
affected by the three dimensional nature of the turbulent wake
flow. This exerts aconsiderable influence on the pressure
distribution and increases the flow-induced forces over
thosepredicted using simple cross-flow theory.
An analysis of the available data15, 44 indicates that in this
flow regime the force coefficients may beestimated using
, (4.7)
, (4.8)
and (4.9)
where is given by Figure 4 and it is assumed that the axial
force CT can be ignored. Appendix C providesequations representing
the data in Figure 4.
0 90
CT /CD0 k 180--------- 2
180--------- =
CD0/CD0 3 CT /CD0sin+cos=
CL0/CD0 2 CT /CD0cossincos=
Re Recrit( )
CN CD0 f=CD0 CN cos=CL0 CN sin=
f
Supercritical region
Equation (4.3) or (4.5)
Equation (4.7) or (4.8)
Subcriticalregion
3 105
CNor
CD0
Ree = T R (V D sec /)10
Sketch 4.2 Variation of force coefficients for inclined
cylinder
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.ESDU 80025The data for in Figure 4 for smooth or relatively
smooth cylinders can be taken to apply up to say
. For very rough cylinders the adverse effect of the roughness
elements causing earlierseparation of the boundary layer from the
cylinder is unlikely to be made significantly worse by
thethree-dimensional wake effects induced by cylinder inclination.
For this reason it is probable that the simplecross-flow theory
described in Section 4.1 can be applied to rough cylinders say (
).Between and 10 103 values of between the two extreme
recommendations arelikely to apply as indicated in Figure 4 and by
the Equations in Appendix C. No data have been found toverify these
tentative recommendations and this is clearly an important area
needing further research.
4.3 Curved Cylinders
Data24 suggest that, for , Equations (4.3), (4.5) and (4.6) may
be applied locally to long, nottoo highly curved cylinders by
taking as the local inclination of the curved cylinder to the
free-streamand then summing the local forces along the cylinder
length. In the absence of any other information asimilar procedure
may be used for using the appropriate data in Section 4.2.
5. CYLINDERS WITH SURFACE IRREGULARITIES
5.1 Stranded Cables
Figure 5 gives drag coefficient data for stranded wire cables as
a function of Reynolds number and the ratioof strand to cable
outside diameter (d/D). The correlation follows the trend of a
collection of data22, 47which show a scatter of about 0.1 in CD0
about the smoothed mean correlation curves. The experimentaldata
indicate that for smooth flow conditions the rapid fall in CD0 with
Re occurs at a Reynoldsnumber of between 2 104 and 3 104. It is not
expected that turbulence will have a very significant effecton CD0
but data47 indicate that for Iu = 0.11 the value of ReD, at which
the rapid fall in CD0 with increasingRe occurs (see Sketch 3.1), is
decreased to about 1 104.
Insufficient data are available for to indicate how CD0 varies
for . Extrapolationof Figure 5 to lower values of d/D is therefore
not recommended.
For stranded cables that are inclined to the approaching flow it
may be assumed that the simple cross-flowtheory described in
Section 4.1 applies. In this case Recrit (based on streamwise
components) can be takenas the value of Re in Figure 5 at which the
rapid fall in CD0 begins.
5.2 Perforated Cylinders and Shrouds
f/D 0.1 10 3/D 0.1 10 3= f
Ree 3 105
Iu 0.01
(a) Perforated cylinder (b) Cylinder enclosed by perforated
shroud11
Sketch 5.1
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.ESDU 80025Perforated cylinders, either in the form of (a) in
Sketch 5.1 or in the form of (b) where a perforated shroudis fitted
over a circular cylindrical structure, can be used to inhibit
flow-induced oscillations. For example,dampers consisting
essentially of a perforated cylinder of 60 per cent open-area ratio
and L/D = 4when attached to overhead cables are often used in
reducing the amplitude of wind-induced gallopingmotions51. The use
of shrouds fitted to the top 25 per cent of circular
cylindricalstructures has also been shown to be effective in
reducing oscillatory motion due to vortex shedding. Theperforations
in the cylinder act to reduce the tendency to shed strong
vortices.
Drag coefficient data for a uniformly perforated cylinder are
presented in Figure 6 as a function of theopen-area ratio . Similar
data for a cylinder enclosed by a perforated shroud are given in
Figure 7. Inthis case data are provided giving CD0 for the
cylinder-shroud combination and the component of this totalCD0
acting on the shroud.
Particular features to note in Figure 6 and 7 are that (i) the
drag coefficient of a perforated cylinder can begreater than that
for an equivalent solid cylinder and (ii) that with shrouded
cylinders the drag coefficientof the inner cylinder can be
negative.
Since the data on which Figures 6 and 7 are based are limited to
specific configurations they have beenextrapolated to other
open-area ratios and cylinder-to-shroud diameters using methods
outlined inSection 5.2.1.
5.2.1 Derivation
Data are available51 for a perforated cylinder with an open-area
ratio of 0.6 and values of L/D from 2.7to 8. An approximate
estimate of the drag of a perforated cylinder is given by
considering two perforatedplates in series using data presented in
Item Nos 70015 and 81027. By comparing these estimates with
themeasured data, a correction factor can be obtained which is
found to be only slightly dependent on L/D.Correction factors for
the extreme cases where and 1.0 can also be determined which,
whencorrelated with the values for , then provide a basis for a
general method of estimating CD for aperforated cylinder from to
1.0. This forms the basis for Figure 6.
For a cylinder enclosed in a perforated shroud, data for
open-area ratios of 20 per cent and 36 per cent areavailable28 for
a range of cylinder-to-shroud diameters from 0.73 to 0.85. Values
of CD0 for both theshroud-cylinder combination and the
contributions acting on the shroud were measured. These data
havebeen extrapolated through to values of the cylinder-to-shroud
diameter ratio equal to zero (given byFigure 6) and unity, when CD0
(at subcritical Re) will be about 1.2 for the cylinder-shroud
combination.Of this total approximately will be the contribution
acting on the shroud when the cylinderand shroud diameters are
equal.
5.3 Effect of Fins and Strakes
Helical strakes of the type fitted to stacks and towers to
inhibit vortex-induced oscillations cause asignificant increase in
the drag coefficient. An analysis of data18 for cylinders fitted
with helical strakesover part of their length shows that a good
estimate of CD for the straked portion can be obtained by
equatingthe strake protrusion height (d) to and using Figures 1 to
3 with the corresponding value of . Typically,for , CD0 = 1.15(1 +
2d/D).
A similar procedure can be used to estimate CD0 for cylinders
with fins or ribs spanning the length of thecylinder at regularly
spaced intervals around the circumference. Section 5.4 provides
guidance on theeffect of isolated spanwise protrusions.
0.6=( ) 0.20 to 0.36=( )
( )
0= 0.6=
0=
1 ( )CD0
/DRe 3 105>12
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.ESDU 800255.4 Effect of Other Spanwise Protrusions
Sketch 5.2 Cylinder with various types of protrusions along its
length
For practical engineering structures it is rare that the outside
surface will be free from surface irregularities.Circular
cylindrical structures are no exception and are often encumbered
with spanwise protrusions suchas pipes, ladders, brackets, overlap
joints and ice droplets many of which can be idealised by the
simpleprotrusion shapes illustrated in Sketch 5.2.
The effect of these spanwise protrusions is twofold. First, the
maximum CD0 of the cylinder with aprotrusion is usually
significantly greater than that of the plain cylinder. Secondly,
the addition of a spanwiseprotrusion causes the configuration to
become asymmetrical with the result that a side force
(representedby CL0) is induced. The physical explanation for the
origin, direction and variation of these forces with Reis
summarised in Section 5.4.1.
Figures 8 and 9 provide data giving the variation of the maximum
values of CD0 and CL0 with Ree ; Figure 10provides guidance on
typical variations of CD0 and CL0 with the angular location of the
protrusion for thesubcritical and supercritical regimes. These data
apply for two-dimensional conditions; the correctionfactors for
finite aspect ratio and shear flow effects from Reference 1 can be
used where necessary. Thecalculation sheets on Tables 10.4 and 10.3
summarise the steps necessary to obtain CD0 and CL0 .
Although there are few data sources dealing with the protrusion
problem it is clear that to a large extentboth the maximum CD0 and
CL0 tend to be independent of the protrusion shape. Data presented
in Figures 8and 9 provide typical values of CD0 and CL0 based on
data for plate-type20, 38, step-type38 andcylindrical-type38
protrusions and closely spaced ice droplets25. It may be assumed,
in the absence of otherinformation, that the maximum values apply
for similarly shaped protrusions although the qualificationsnoted
later for steps should be taken into account.
In some situations a gap may exist between the protrusion and
the cylinder surface (e.g. as with a piperunning along the cylinder
length). In this case, providing the gap width (h) is not large
(less than about0.25 D) the data in Figures 8 to 10 can be assumed
to apply approximately by taking the protrusion height
CL0
V
CD0
Defined as positive when directed awayfrom 'upper surface' as
depicted in sketch
Protrusion typeCD0CL0
PlateridgeFig. 8, 10Fig. 9, 10
CylindricalridgeFig. 8, 10Fig. 9, 10
Icingdroplet ridgeFig. 8, 10Fig. 9, 10
Protrusion typeCD0CL0
2 plateridgesFig. 10Fig. 10
Forwardfacing stepFig. 8 1.15Fig. 9
Rearwardfacing stepFig. 8 1.15See text
(d droplet height)13
as d + h.
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.ESDU 80025The original data were obtained in low turbulence
flow but the application of Figures 8 and 9has been tentatively
extended to cover other conditions using the effective Reynolds
number
to correlate the data. In this way the turbulence factor
(Section 3.2) can be used toaccount for the effect of turbulence in
the approaching flow. In addition the factor (Section 3.1) canbe
used to account approximately for the effect of slightly rough
surfaces (up to ) but forrougher surfaces it is likely that the
addition of a protrusion invalidates the use of as given by Figure
2.
For forward-facing or rearward-facing steps (typical of overlap
joints generated when a metal sheet is rolledinto a cylinder) the
data38 indicate that CD0 is approximately 15 per cent higher than
the values given inFigure 8 for subcritical Reynolds numbers . The
CL0 data are less well defined and arebased only on data for plate
protrusions20 (supercritical Re) and forward-facing steps38
(subcritical Re).For a rearward facing step, and subcritical Re,
CLmax appears to be up to about 50 per cent greater than thevalues
given in Figure 9 for values of d/D greater than 0.03. At
supercritical it maybe assumed that there is no dependence on
protrusion shape within the limited applicability of Figure 9.
5.4.1 Comments on the effects of protrusions
The variation of CD0 with Re for a cylinder with a protrusion is
similar to that for a plain cylinder but withsome important
differences which are also associated with the occurrence of
significant values of CL0. Aswith the plain cylinder CD0 is a
maximum at lower values of Re but its variation with Re goes
through twotransition stages. A premature boundary layer transition
to turbulent flow on the upper surface (withreference to Sketch
5.2) is caused by turbulence produced by the protrusion element and
results in delayedflow separation, larger suction pressures, higher
base pressure and an initial decrease in CD0 with increasingRe.
This is followed at a higher Re (corresponding approximately to
Recrit for a smooth cylinder) by afurther drop in CD0 as the lower
surface boundary layer becomes turbulent at separation.
At subcritical Re the larger suction pressures on the upper
surface (due to the delayed boundary layerseparation) cause the
lift force to be positive (i.e. directed upwards). At supercritical
Re the protrusioncauses a larger separated flow region to occur on
the upper surface, thus eliminating its region of highsuction
pressures, but increases the suction pressures on the lower surface
(typically by about 30%); thisresults in a negative lift force
(directed downwards). The maximum CL0 occurs at just supercritical
Re(giving negative CL0) when there is a maximum differential
between the flow separation points on the upperand lower surfaces.
In general the maximum values of CD0 and CL0 do not occur for the
samecircumferential position of the protrusion; except at high Re,
CLmax tends to occur for a value of at whichCD0 is a minimum, and
vice versa.
Iu 0.005
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.ESDU 800256. PROXIMITY EFFECT OF PLANE SURFACE PARALLEL TO
CYLINDER AXIS
Sketch 6.1 Cylinder near plane surface
Interference effects associated with the proximity of a plane
surface parallel to the longitudinal axis of acircular cylinder
occur in various practical situations such as with pipe lines on
the sea bed or with stackslocated near a boiler house wall. The
proximity of the plane surface not only causes large variations in
CD0but also induces significant side forces (CL0) associated with
the asymmetry of the flow which acts to repelthe cylinder from the
surface.
The calculation sheet in Table 10.4 provides a summary of the
steps to obtain CD0 and CL0 given inFigures 11 and 12. These data
provide information for an idealised situation; in practice
conditions maybe significantly different from this and in such
circumstances the data should only be used as a guide. Notein
particular that is the local free-stream velocity which in the
presence of other nearby surfaces orobstructions may be
significantly different from the undisturbed free-stream
velocity.
The information presented in Figures 11 (h = 0) and 12 is based
on limited sources33, 42, 45, 49 givingthe mean value of CD0 and
CL0 for a range of values of h/D and Re. The data apply to long
cylinders whereend effects can be ignored.
Figure 11 deals with the case when the cylinder is resting on
the surface. The forces induced are dependenton the thickness of
the boundary layer on the surface just upstream of the cylinder
location. These boundarylayer effects can be approximately
accounted for if CD0 and CL0 are defined as the mean drag or lift
forceper unit length/ where Veff is a mean effective velocity given
by
(6.1)
which, assuming that , gives
. (6.2)
Values of for a turbulent boundary layer on a smooth flat plate
can be obtained from Item No. 680202or from the correlating
equation representing these data:
. (6.3)
CL0V
Vz
h
CD0z
V
h 0>( )
V2eff D( )
V2effV
2----------- 1
D---- Vz
2 /V2 zd
h
D h+=
Vz/V Vz/V z/( )= = for /h 1( )
V2effV
2-----------
D---- 1
2 + 1----------------- 1h/D/D---------
2 + 1 1 hD----D----+ +=
---- x---- -- 0.078 10 Rexlog( )1.06
----------------------------------------------------------
x----= =15
D D x 1 3.03 10 Rexlog( ) 1.06 D
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.ESDU 80025Here and x is the distance from the origin of the
turbulent boundary layer to the point atwhich is required but for
the present application it can be taken as the distance from the
leading edge ofthe plane surface.
Figure 11 is based on data obtained in smooth free-stream flows
but it is not expected that greater free-streamturbulence will have
a significant effect on the variation of CD0 or CL0 with Re for h =
0. The drop in CD0at is associated with the transition to turbulent
flow in the cylinder upper surface boundary layerat separation.
This is accompanied by a rearward movement of the separation point
and coincides with theoccurrence of the maximum value of CL0 .
The data in Figure 11 (for h = 0) apply when the surface of the
cylinder is nominally smooth. Someevidence33 suggests that
increasing surface roughness tends to increase CD0 only slightly at
but to decrease CL0 for as indicated by the tentative values in
Figure 11.
Figure 12 provides a means for estimating CD0 and CL0 when a gap
exists between the cylinder and thesurface and is based on a
correlation of existing data. For a gap width of less than about
0.3D periodicvortex shedding is suppressed but for gaps only
slightly greater than this it appears49 that the vortex
sheddingprocess becomes more finely tuned than normal which could
cause serious oscillatory problems for a lightlydamped structure.
For gap widths greater than about 0.5D there is a close
correspondence with the flowabout two cylinders side-by-side (gap =
2h). This could be expected from mirror image
considerations.However, this similarity does not apply for gaps
less than about 0.5D since, in particular, the wall boundarylayer
separates upstream of the cylinder and induces an additional
inclination in the approaching flow (seeSketch 6.2) which is not
present in the flow about two side-by-side cylinders.
Sketch 6.2 Flow pattern around cylinder near surface
The separated flow regions upstream and downstream of the
cylinder will cause scouring on either side ofa horizontal pipeline
placed on a sea bed. Minimum pressure coefficients on the surface
plane of about0.5 at A for h/D = 0 and 0.8 and 0.5 at B for h/D =
0.4 and 1.0 respectively have been measured49.
Rex Vx/=
Re 105
Re 2 105>Re 3 105>
16
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.ESDU 800257. MEAN AND FLUCTUATING PRESSURE DISTRIBUTIONS,
VELOCITY FLOW FIELD
A knowledge of the pressure distribution around a circular
cylindrical structure is important in some aspectsof design
particularly those where the local pressures on cladding or glazing
elements are required. Methodsfor estimating the mean pressure
distribution, and its fluctuating component, are given in Sections
7.1and 7.2 for . This pressure distribution relates to conditions
at the surface of the cylinder.However, in some design situations
the velocity distribution in the flow field around, and away from,
thecylinder surface is also required. This arises, for example, in
assessing wind velocity amplification factorsapplicable to the
estimation of wind forces acting on dish aerials attached to
towers. Guidance on thisaspect is provided in Section 7.3.
The calculation sheet in Table 10.5 summarises the various steps
of the procedure but for repetitivecalculations the whole method
may be simply programmed using the equations in the following
Sectionsand in Appendix C.
7.1 Mean Pressure Distribution at Surface
Sketch 7.1 Pressure distribution parameters
The method for estimating the pressure distribution is
applicable for and is based onEquations (7.1) to (7.3) and a
knowledge of the four parameters Cpb, , Cpm and shown in Sketch
7.1.These parameters are given by the empirical correlations in
Figures 13 and 14 and a specified value of CD0which may be
estimated from Section 3 as a function of the free-stream
properties (Re and turbulencecharacteristics) and the roughness of
the cylinder surface. The derivation of the method is described
inSection 7.1.1. The main steps of the calculation procedure
(summarised in the calculation sheet inTable 10.5) for a
two-dimensional cylinder are as follows.
(1) Estimate CD0 using the procedure in Section 3.3 (or the
calculation sheet, Table 10.3).
(2) Obtain Cpb from Figure 13a, from Figure 13b and from Figure
14a.
(3) Calculate and obtain Cpb Cpm from Figure 14b and hence
evaluate Cpm.
Re 3 104>
V
Cp
Cpm
Cpb
+1
00 180
m b
Re 3 104>b m
b mb m17
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.ESDU 80025(4) Calculate values of Cp at other values of as
required from Equations (7.1) to (7.3).
For . (7.1)
For . (7.2)
For . (7.3)
For a cylinder of finite length with a free end the pressure
distribution over the portion of the cylinder awayfrom the tip
region (i.e. more than two diameters from the tip) is given by the
same procedure except that(i) in estimating Cpb from Figure 13a the
local value of CD is used (see Reference 1) and (ii) the value
of
is determined from Figure 13b using the value of Cpb estimated
from Figure 13a assuming that thecylinder is two-dimensional.
Further guidance on the estimation of pressure distributions on
finite-lengthcylinders is given in Reference 1.
7.1.1 Derivation of method for mean pressure distribution at
surface
The theoretical wake source model of Parkinson and Jandali30 can
be used to obtain predictions of thepressure distribution around
the surface of a circular cylinder providing that Cpb and the
separation pointcan be specified. The pressure coefficient at any
point is then a function only of these parameters and thelocal
value of . In particular the results of applying the method show
that, to a close approximation,unique correlations exist between
and * (and by implication *) and between Cpb Cpm and
. In practice, however, there are some differences between these
theoretically derivedrelationships and experimental correlations of
data. These differences are associated with the boundarylayer and
principally occur when the boundary layer at separation is laminar.
The correlations presentedin Figures 13 and 14 have thus been based
on experimental data but they only depart from the trend of
thetheoretically derived data when Cpb Cpm and are small.
In order to provide a simple method of calculating Cp (and ) at
any other value of , the theoreticalinviscid potential flow
solution (for which Cp = 1 (1 Cpm) and Cpm = 3) has been modified
tofit the known or estimated values of Cp at , and . This then
leads to the pressure distributionsrepresented by Equations (7.1)
to (7.3) which have been found to represent data from wind-tunnel
tests andfull-scale measurements extremely well.
7.2 Fluctuating Pressure Distribution at Surface
The pressure on the surface of a circular cylinder fluctuates
with time for two main reasons. First, theperiodic process of
shedding vortices induces unsteadiness into the flow. Secondly,
turbulence in theapproaching flow causes fluctuations in the
approach flow velocity and direction. The spectra of thepressure
fluctuations originating from vortex shedding in the wake will be
dissimilar to those of the incidentturbulence particularly in the
base region. However, the component of the pressure fluctuations
due to theincident turbulence will respond in a quasi-steady way to
the instantaneous changes in free-stream velocityand direction
(which induces an effective change in ).
* Whilst is the angular position of the separation point,
represents the angular position when the local value of Cp first
equals
0 m : Cp 1 1 Cpm( ) 2 m------ 90sin=
m b : Cp Cpb Cpb Cpm( ) 2 mb m----------------- 90cos=
b 180 : Cp Cpb=
b
m sep b
sep m
b mdCp/d
2sin 0= m b
18
Cpb. In practice is greater than by about 5 to 10.sep bb sep
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.ESDU 80025In general, a turbulent incident flow (Iu greater
than about 0.1) causes the vortex shedding process to berandom in
nature. The magnitude of the pressure fluctuations is then
determined primarily by a quasi-steadyresponse to the velocity
fluctuations in the approaching flow. In particular this will apply
for supercriticalReynolds numbers and especially when the scale of
turbulence is much greater thanthe cylinder diameter. However, if
the cylinder is oscillating with significant amplitudes (greater
than about0.03D), or the Reynolds number is subcritical , then the
vortex shedding process is moreregular; the pressure fluctuations
will then reflect to a greater extent the velocity fluctuations
induced bythe periodic shedding of vortices. Thus (as found by
comparisons with experimental data40, 50) thefollowing quasi-steady
theory is most likely to be applicable to non-oscillating
structures at high Re inturbulent flows such as the atmospheric
wind.
Quasi-steady theory predicts that for a vertical structure the
mean square of the fluctuating pressurecoefficient due to
turbulence in the approaching flow is given by*
. (7.4)
Ignoring second order terms, the standard deviation of the
fluctuating pressure coefficient is given by*
(7.5)
where typical values of the turbulence intensities Iu and Iv are
given in Table 10.2 and values of may be derived by differentiating
Equations (7.1) to (7.3) when the following equations result.
For . (7.6)
For . (7.7)
For . (7.8)
An extreme value of the fluctuating pressure coefficient is
given by
(7.9)
where g is a crest, or peak, factor which typically has a value
of about 3.
* The first term on the right-hand side of Equations (7.4) and
(7.5) accounts for the fluctuations in free-stream velocity. The
second term,for a vertical structure, accounts for the fluctuations
in free-stream direction in the cross-sectional plane of the
cylinder. In this latter
Re 6 105>( ) Lr u( )Re 3 105( )
p t( )V2------------------
2 V u t( )+( )2
V2-------------------------------------- Cp
2dCpd---------
v t( )V---------
2
+=
Cp 2IuCp( )2dCpd---------Iv
2+
=
dCp/d
0 m
CD0 Ree 3.105
CL0f
Ree 3.105>
1.2 2 cos> CN 1.2 2 cos=CD0
CL0
23
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.ESDU 800258.4 Calculation Sheet for Example 1 (from Table
10.5)
Pressure Coefficients and Local Velocities
MEAN PRESSURE COEFFICIENT (Section 7.1)
63 CD0 (steps 1 19) 0.56
64 Cpb (Fig. 13a) 0.61
65 (Fig. 13b) deg. 118.7
66 (Fig. 14a) deg. 80.2
67 deg. 38.5
68 Cpb Cpm (Fig. 14b) 1.18
69 Cpm 1.79
70 deg. 80.2
71 Cp (Eqn. (7.1), (7.2) or (7.3)) 1.79
FLUCTUATING PRESSURE COEFFICIENT (Section 7.2)
72 Iu (Table 10.2) 0.15
73 Iv (Table 10.2) 0.12
74 (Eqn. (7.6), (7.7) or (7.8)) 1/deg. 0
75 (Eqn. (7.5)) 0.54
76 (Eqn. (7.9)) 3.41
VELOCITY FIELD AWAY FROM SURFACE (Section 7.3)
77 m/s 30
78 deg. 80.2
79 r/D 0.75
80 Cp at surface (step 71) 1.79
81 m/s 50.1
82 Fig. 15a 0.65
83 m/s 37.0
84 Fig. 15b 0.35
85 deg. 9.8
86 deg. +6.4
bmb m
dCp /d
Cp
Cp t( )
V
Vs V 1 Cp( )=
Vs V r ;( )( )/ Vs V( )
V r ;( )s r ;( )( )/s
s 90 =
r ;( )24
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.ESDU 800259. REFERENCES AND DERIVATION
9.1 References
The References given are recommended sources of information
supplementary to that in this Data Item.
9.2 Derivation
The Derivation lists selected sources that have assisted in the
preparation of this Data Item.
1. ESDU Mean forces, pressures, and moments for circular
cylindrical structures: finite-lengthcylinders in uniform and shear
flow. Item No. 81017, 1981.
2. ESDU The compressible two-dimensional turbulent boundary
layer, both with and without heattransfer, on a smooth flat plate,
with application to wedges, cylinders and cones. ItemNo. 68020,
1968. (Contained in the Aerodynamics Sub-series.)
3. ESDU Characteristics of atmospheric turbulence near the
ground. Part I: definitions andgeneral information. Item No. 74030,
1974.
4. ESDU Characteristics of atmospheric turbulence near the
ground. Part II: single point data forstrong winds (neutral
atmosphere). Item No. 85020, 1985
5. ESDU Characteristics of atmospheric turbulence near the
ground. Part III: variations in spaceand time for strong winds
(neutral atmosphere). Item No. 86010, 1986.
6. ESDU Lattice structures. Part 2: mean fluid forces on
tower-like space frames. ItemNo. 81028, 1981
7. ESDU Calculation methods for along-wind loading. Part 2.
Response of line-like structures toatmospheric turbulence. Item No.
87035, 1987.
8. ESDU Response of structures to vortex shedding. Structures of
circular or polygonal crosssection. Item No. 96030, 1996.
9. ESDU Blockage for bluff bodies in confined flows. Item No.
80024, 1980.
10. RELF, E.F. Discussion of the results of measurements of the
resistance of wires, with someadditional tests on the resistance of
wires of small diameter. ARC R & M 102,Aeronautical Res.
Council, UK, March 1914.
11. RELF, E.F.POWELL, C.H.
Tests on smooth and stranded wires inclined to the wind
direction, and a comparison ofresults on stranded wires in air and
water. ARC R & M 307, Aeronautical Res. Council,UK, January
1917.
12. WIESELSBERGER, C. New data on the laws of fluid resistance.
NACA Tech. Note 84, April 1921.
13. FAGE, A.WARSAP, J.H.
The effects of turbulence and surface roughness on the drag of a
circular cylinder. ARCR & M 1283, Aeronautical Res. Council,
UK, October 1929.
14. FAGE, A. Drag of circular cylinders and spheres. ARC R &
M 1370, Aeronautical Res. Council,UK, May 1930.
15. BURSNALL, W.J.LOFTIN, L.K.
Experimental investigation of the pressure distribution about a
yawed circular cylinderin the critical Reynolds number range. NACA
Tech. Note 2463, June 1951.25
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.ESDU 8002516. GOWEN, F.E.
PERKINS, E.W.Drag of circular cylinders for a wide range of
Reynolds numbers and Mach numbers.NACA Tech. Note 2960, March
1952.
17. DELANY, N.K.SORENSEN, N.E.
Low-speed drag of cylinders of various shapes. NACA Tech. Note
3038, August 1953.
18. COWDREY, C.F.LAWES, J.A.
Drag measurements at high Reynolds numbers of a circular
cylinder fitted with threehelical strakes. NPL Aero. Rep. 384,
National Physical Laboratory, England, July 1959.
19. TRITTON, D.J. Experiments on the flow past a circular
cylinder at low Reynolds number. J. FluidMech., Vol. 6, pp.
547-567, 1959.
20. LOCKWOOD, V.E.McKINNEY, L.W.
Effect of Reynolds number on the force and pressure distribution
characteristics of atwo-dimensional lifting circular cylinder. NASA
Tech. Note D-455, September 1960.
21. ROSHKO, A. Experiments on the flow past a circular cylinder
at very high Reynolds number. J. FluidMech., Vol. 10, pp. 345-356,
1961.
22. COUNIHAN, J. Lift and drag measurements on stranded cables.
Imperial College, University ofLondon, Aeronaut. Dept. Rep. 117,
August 1963.
23. DENNIS, S.C.R. The steady flow of a viscous fluid past a
circular cylinder. ARC 26, 104, AeronauticalRes. Council, UK,
August 1964.
24. SURRY, J. Experimental investigation of the characteristics
of flow about curved circularcylinders. University of Toronto,
UTIAS Tech. Note 89, April 1965.
25. SIMPSON, A.LAWSON, T.V.
Oscillations of twin power transmission lines. Paper 25, Proc.
Symp. on Wind Effectson Buildings and Structures, Loughborough
Univ., April 1968.
26. BEARMAN, P.W. The flow around a circular cylinder in the
critical Reynolds number regime. NPL Aero.Rep. 1257, National
Physical Lab., UK, January 1968.
27. ACHENBACH, E. Distribution of local pressure and skin
friction around a circular cylinder in cross-flowup to Re = 5 106.
J. Fluid Mech., Vol. 34, pp. 625-639, 1968.
28. KNELL, B.J. The drag of a circular cylinder fitted with
shrouds. NPL Aero Rep. 1297, NationalPhysical Lab., England, May
1969.
29. JONES, G.W.CINCOTTA, J.J.
Aerodynamic forces on a stationary and oscillating cylinder at
high Reynolds numbers.NASA Tech. Rep. R-300, 1969.
30. PARKINSON, G.V.JANDALI, T.
A wake source model for bluff body potential flow. J. Fluid
Mech., Vol. 40, Pt. 3,pp. 577-594, 1970.
31. ACHENBACH, E. Influence of surface roughness on the
cross-flow around a circular cylinder. J. FluidMech., Vol. 46, Pt.
2, pp. 321-335, 1971.
32. WARSHAUER, K.A.LEENE, J.A.
Experiments on mean and fluctuating pressures of circular
cylinders at cross flow atvery high Reynolds numbers. Papers II.13
of Proc. Third Int. Conf. on Wind Effects onBuildings and
Structures, Tokyo. Saikon Co. Ltd, 1971.
33. JONES, W.T. Forces on submarine pipelines from steady
currents. Paper 71-UnT-3, ASME Conf. onPetroleum Mech. Engng. with
Underwater Tech., Houston, Texas, June 1971.
34. WILSON, J.F.CALDWELL, H.M.
Force and stability measurements on models of submerged
pipelines. Trans ASME, J.Engng. Industry, Vol. 93, No. 4, pp.
1290-1298, November 1971.
35. BUBLITZ, P. Unsteady pressures and forces acting on an
oscillating circular cylinder in transverseflow. Proc. Symp. on
Flow-induced Structural Vibrations, Karlsruhe, Germany,26
pp. 443-453. Springer-Verlag, August 1972.
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.ESDU 8002536. van NUNEN, J.W.G. Pressures and forces on a
circular cylinder in a cross flow at high Reynolds number.
Proc. Symp. on Flow-induced Structural Vibrations, Karlsruhe,
Germany, pp. 748-754.Springer-Verlag, August 1972.
37. SURRY, D. Some effects of intense turbulence on the
aerodynamics of a circular cylinder atsub-critical Reynolds number.
J. Fluid Mech., Vol. 52, Pt. 3, pp. 543-563, 1972.
38. JAMES, D.F.TRUONG, Q.
Wind load on cylinder with spanwise protrusion. Proc. Am. Soc.
Civil Engrs, J. EngngMech. Div., No. EM 6, pp. 1573-1589, December
1972.
39. BATHAM, J.P. Pressure distributions on circular cylinders at
critical Reynolds numbers. J. FluidMech., Vol. 57, Pt. 2, pp.
209-228, 1973.
40. TUNSTALL, M.J. Some measurements on the wind loading on
Fawley Generating Station Chimney. Proc.Symp. on Full-scale Fluid
Dynamic Measurements, Leicester Univ, England, pp. 26-41,1974.
41. MILLER, B.L.MAYBREY, J.F.SALTER, I.J.
The drag of roughened cylinders at high Reynolds numbers.
Division of MaritimeScience, National Physical Lab., England,
Report Mar. Sci. R 132, April 1975.
42. ROSHKO, A.STEINOLFSON, A.CHATTOORGOON, V.
Flow forces on a cylinder near a wall or near another cylinder.
Paper IV, Proc. 2nd U.S.Nat. Conf. on Wind Engng. Res., Colorado
State Univ., June 1975.
43. BRUNN, H.H.DAVIES, P.O.A.L.
An experimental investigation of the unsteady pressure forces on
a circular cylinder in aturbulent cross flow. J. Sound Vib. Vol.
40, No. 4, pp. 535-560, June 1975.
44. TRIMBLE, T.H.MALONE, P.T.
The normal, tangential, lift and drag forces measured near R =
105 on some circularcylinders inclined to large angles in an
airstream. Aero Tech. Memo. 291, AeronauticalRes. Labs, Australia,
July 1975.
45. GOKTUN, S. The drag and lift characteristics of a cylinder
placed near a plane surface. Ph. D. Thesis,Naval Postgraduate
School, Monterey, Calif., December 1975.
46. GUVEN, O. An experimental and analytical study of
surface-roughness effects on the mean flowpast circular cylinders.
Ph.D. Thesis, Univ. Iowa, December 1975.
47. PRICE, S.J. The origin and nature of the lift force on the
leeward of two bluff bodies. Aeronaut.Quart., Vol. 27, Pt. 2 pp.
154-168, May 1976.
48. RUSCHEWEYH, H. Wind loadings on the television tower,
Hamburg, Germany. J. Indust. Aerodyn., Vol. 1,No. 4, pp. 315-333,
August 1976.
49. BEARMAN, P.ZDRAVKOVICH, M.M.
Flow around a circular cylinder near a plane boundary. J. Fluid
Mech., Vol. 89, Pt. 1,pp. 33-47, 1978.
50. CHRISTENSEN, O.ASKEGAARD, V.
Wind forces on and excitation of a 130-m concrete chimney. J.
Indust. Aerodyn., Vol. 3,No. 1, pp. 61-77, March 1978.
51. ALRIDGE, T.R.PIPER, B.S.HUNT, J.C.R.
The drag coefficient of finite-aspect-ratio perforated circular
cylinders. J. Indust.Aerodyn., Vol. 3, No. 4, pp. 251-257,
September 1978.
52. BURESTI, G. The effect of surface roughness on the flow
regime around circular cylinders. Proc. 4thColloquium on Indust.
Aerodynamics, Pt. 2, pp. 13-28, Aachen, June 1980.27
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28
ESDU
80025Surfaces
ate the same drag coefficient in a particularccur. A range of
values, and recommended
2 3 4 6 810-2 10-1
Heavy rust10. TABLES
TABLE 10.1 Typical Values of Effective Roughness Height for a
Number of Common
The effective roughness height represents an equivalent,
uniformly distributed sand grain roughness that would
generturbulent flow as the natural surface roughness itself. It is
an approximate equivalence and large variations in can oaverages
values ( ) are shown above. See also comments in Section 3.1 and
Appendix B.
2 3 4 6 8 2 3 4 6 8 2 3 4 6 8 2 3 4 6 810-6 10-5 10-4 10-3
0 (metres)
Glass : plastic
Drawn metals
Concrete
Cast iron
Brickwork
Marine roughness (rust,barnacles but not seaweed)
Metal, painted
Sheet metal*
Steel, uncoated
Steel, galvanised
Timber
Smoothfinish
Sprayfinish
New smooth
Newsmooth
Newrough
Light rust
Newsmooth
Newrough
Newsmooth
Rough
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The intensity and scale of turbulence are very dependent on the
proximity of turbulence producing elementssuch as buildings or
obstructions in ducts. The values given in the Table are an
approximate guide andvalues close to obstructions may vary
considerably from those given. Turbulence generated by a
buildingwill take about 10 building lengths do die out.
TABLE 10.2 Typical Turbulence Characteristics* for Some General
Environments
* More precise values of turbulence intensity and scale lengths
for strong winds, as a function of height and surfaceroughness, are
given in References 4 and 5.
IntensitiesIuIv
Lateral ScalerLu (metres)
Height above ground (metres) 10 30 100 300 10 30 100 300
Open sea; large stretches of open water.
0.110.07
0.100.06
0.080.05
0.050.04
40 55 95 140
Rural areas; open country with few, low, obstacles.
0.180.12
0.160.10
0.110.08
0.070.06
30 45 70 110
Low density built-up areas;small towns; suburbs; openwoodland
with small trees.
0.250.19
0.190.15
0.140.11
0.080.07
25 40 60 95
Town and city centres with high density of buildings;broken
country with tall trees.
0.350.29
0.240.20
0.160.14
0.090.08
20 30 55 85
Low-turbulence wind tunnel.0.1 duct diameters
Average wind tunnel. 0.001 0.01
Straight duct with fully-developedturbulent flow,30 diameters
downstreamof disturbance.
0.04 0.1 duct diameters
Straight duct, 5-6 diameters downstream of a bend. 0.05
0.05 0.1duct diameters
Near a circular-arc bend withbend radius duct diameter. 0.10
Near a mitred bend. 0.15
0.001 T 1.0Tcrit
T 1( )/ Tcrit 1( )T
CD0/ 1 2/D+( )
Ree 3 105
Ree 3 105>
CD0 Ree 3.105CL0f
Ree 3.105>
1.2 2 cos> CN 1.2 2 cos=CD0CL0
30
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.ESDU 80025TABLE 10.4 Calculation Sheet 2 Mean Force
Coefficients (Continued)
STANDARD CABLE (Section 5.1)
33 d/D
34 deg.
35
36 CD0 (Fig. 5)
37
38 (see Sect. 5.1 for effect of turbulence)
CYLINDER WITH PERFORATIONS OR STRAKES (Sections 5.2 and 5.3)
39 Re (step 10) or Ree (step 17)
40 Perforated cylinder:
41 Perforated cylinder: CD (Fig. 6)
42 Cylinder with perforated shroud: CD0 (Fig. 7)
43 Perforated shroud: CD0 (Fig. 7)
44 Cylinder with helical strakes (Sect. 5.3)
45 CD0 (Fig. 1c with )
CYLINDER WITH ISOLATED SPANWISE PROTRUSIONS (see Sketch 5.2 in
Sect. 5.4 for applicability)46 d/D
47 deg.
48 Ree (steps 117)
49 CD0max or CD0 (Fig. 8, 10)
50 CL0max or CL0 (Fig. 9, 10)
CYLINDER NEAR PLANE SURFACE (Section 6)51 h/D
52 x/D
53
54 ( , for smooth surface)
55 (Eqn. (6.3))
56 Veff (Eqn. (6.2)) m/s
57 Reeff = VeffD/
58 CD0h = 0 (Fig. 11a)
59 CL0h = 0 (Fig. 11b)
60 CD0 (step 19) based on
61 CD0h (Fig. 12a)
62 CL0h (Fig. 12b)
Re VD /sec=
CN CD0 2cos=
d=
Rex V x/= 0.1/D
V 2eff31
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TABLE 10.5 Calculation Sheet 3 Pressure Coefficients and Local
Velocities
MEAN PRESSURE COEFFICIENT (Section 7.1)
63 CD0 (steps 119)
64 Cpb (Fig. 13a)
65 (Fig. 13b) deg.
66 (Fig. 14a) deg.
67 deg.
68 Cpb Cpm (Fig. 14b)
69 Cpm
70 deg.
71 Cp (Eqn. (7.1), (7.2) or (7.3))
FLUCTUATING PRESSURE COEFFICIENT (Section 7.2)
72 Iu (Table 10.2)
73 Iv (Table 10.2)
74 (Eqn. (7.6), (7.7) or (7.8)) 1/deg.
75 (Eqn. (7.5))
76 (Eqn. (7.9))
VELOCITY FIELD AWAY FROM SURFACE (Section 7.3)
77 m/s
78 deg.
79 r/D
80 Cp at surface (step 71)
81 m/s
82 Fig. 15a
83
84 Fig. 15b
85 deg.
86 deg.
bmb m
dCp /dC p
Cp t( )
V
Vs V 1 Cp( )
=
Vs V r ;( )( )/ Vs V( )
V r ;( )s r ;( )( )/s
s 90 = r ;( )32
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ESDU product issue: 2007-01. For current status, contact ESDU.
Observe Copyright.
ESDU
80025
2 3 4 5 6 7 8 102
imensional conditions%33
FIGURE 1a DRAG COEFFICIENT AT LOW REYNOLDS NUMBERS
Re
2 3 4 5 6 7 8 2 3 4 5 6 7 8 2 3 4 5 6 7 810-2 10-1 100 101
CD0
2
3
4
5678
2
3
4
5678
2
3
4
5678
100
101
102
103
(a) 10-2 < Re < 102
1
Applicability : 2-dUncertainty : 10
V
/D small
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Observe Copyright.
ESDU
80025
ERS
2 3 4 5 6 7 8 9105
ility : 2-dimensional conditionsty : 0.06 in CDo34
FIGURE 1b DRAG COEFFICIENT AT INTERMEDIATE REYNOLDS NUMB
Ree = TRRe2 3 4 5 6 7 8 9 2 3 4 5 6 7 8 9102 103 104
CD0
1 + 2
0.0
0.4
0.8
1.2
1.6
2.0
2.4
2.8
(b) 102 < Ree < 105
ApplicabUncertain
D
V
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Observe Copyright.
ESDU
80025
2 3 4 5 6 7 8 9 108
6040
20105
21.4
1.0
0.6
0.4
0.2
0.1
3
0.010.002
(/D) 103
10.1
data
nal conditionsee < 5 10
5; +10% - 30% of CDo Ree; 0.06 in CDoendix C 35
FIGURE 1c DRAG COEFFICIENT AT HIGH REYNOLDS NUMBERS
Ree = TRRe2 3 4 5 6 7 8 9 2 3 4 5 6 7 8 9105 106 107
CDo
1 + 2
0.0
0.2
0.4
0.6
0.8
1.0
1.2
1.4
D
For values of see Table Extrapolated
Applicability : 2-dimensioUncertainty 3 105 < Rin CDo All
other
Eqns. to curves : See App
}
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Observe Copyright.
ESDU
80025
2 3 4 5 6 7 8 102
: 10% in Rves : See Appendix C
Extrapolated data36
FIGURE 2 ROUGHNESS FACTOR
D
2 3 4 5 6 7 8 2 3 4 5 6 7 8 2 3 4 5 6 7 810-2 10-1 100 101
R
1.0
2.0
3.0
4.0
5.0
6.0
7.0
103 1042 3 4 5 6 80
0.2
0.4
0.6
0.8
1.0
7
Ree
UncertaintyEqns to cur
(a) Ree > 104
1
103
R - 1R (Fig. 2a) - 1
(b) Ree < 104
R
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FIGURE 3 TURBULENCE FACTOR FOR DEFINING Ree
Iu(D / rLu)
0.2
2 3 4 5 6 7 8 2 3 4 5 6 7 8 2 3 4 5 6 7 810-3 10-2 10-1 100
Tcrit
1
2
3
4
5
6
7
8
9
10
11
12
13
(a) Effect of turbulence on Tcrit
ReRecrit
2 3 4 5 6 7 8 2 3 4 5 6 7 8 2 3 4 5 6 7 810-1 100 101 102
T - 1Tcrit - 1
0.0
0.1
0.2
0.3
0.4
0.5
0.6
0.7
0.8
0.9
1.0
1.1
1.2
1.3
(b) Effect of turbulence on Tcrit
For equations to these curves - see Appendix C37
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FIGURE 4 FACTOR GIVING NORMAL FORCE COEFFICIENT FOR INCLINED
CYLINDERS AT SUPERCRITICAL REYNOLDS NUMBERS
0 20 40 60 80 100
f
0.2
0.4
0.6
0.8
1.0
1.2
0.1
0.5
1
5
10
/ D H 103
Applicability : 2 - dimensional flow: Ree > 3 x 105
Uncertainty : 10% in f for (/D) < 0.1 x 10-3Eqns. to curves :
See Appendix C
Tentative values ( see Section 4.2)
CN = f (CD0)=0
CL0
CD0
CN
V38
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Observe Copyright.
39
ESDU
80025
2 3 4 5 6 7 8 9 106
( For Iu 0.1 see Section 5.1)D0 unless indicatedFIGURE 5 DRAG
COEFFICIENTS FOR ISOLATED STRANDED CABLES
Re
2 3 4 5 6 7 8 9 2 3 4 5 6 7 8 9103 104 105
CD0(based on D)
0.6
0.8
1.0
1.2
1.4Scatter band of CDo data
dD
0.3
0.2
0.15
0.1
0.07
Applicability : Iu < 0.01 Uncertainty : 0.05 in C
otherwise
V
D
d
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.ESDU 80025
FIGURE 6 DRAG COEFFICIENTS FOR UNIFORMLY-PERFORATED CIRCULAR
CYLINDERS
(= Open area ratio)0.2 0.4 0.6 0.8 1.0
CD
0.0
0.2
0.4
0.6
0.8
1.0
1.2LD
20
5
3
10
Applicability : < 0.1, 3104 < Ree < 3105 only > 0.2,
effect of Re likely to be small for all Ree > 310
4
Uncertainty : Solid lines 5% Dashed lines 10%
L
D
Re < ReD40
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FIGURE 7 DRAG COEFFICIENTS FOR SHROUD-CYLINDER COMBINATIONS
DcylDshroud
0.2 0.4 0.6 0.8 1.0
CD0 (based on Dshroud); Re =3 H 105
0.0
0.2
0.4
0.6
0.8
1.0
1.2
0.36
0.20
0.20
0.36
1.0
0
Open area ratio Re < ReD
Applicabilty : 2-dimensional shroud
Uncertainty : 10%
CD0 of shroud (with cylinder inside)CD0 of cylinder + shroud
Re
2 3 4 6 8 2 3 4105 106
CD0 at Re
CD0 at Re = 3 H 1050.9
1.0
DcylDshroud
0.2
0.36
= 0.81 only
Dshroud
Dcyl41
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Observe Copyright.
42
ESDU
800252 3 4 5 6 7 8 9 107
o
30 to 90
60 to 8090
30 to 90dD = 0 (smooth cylinder)
} 10%D
er curve (or curves) gives them CDor values of see Figure 10
See Sketch 5.2; < 0.05 x 10-3
ee < 3 105
ee > 6 105
x 105 < Ree < 6 x 105, 20%
trapolated or interpolated data
D
} 10%
Location of protrusion
FIGURE 8 EFFECT OF SINGLE SPANWISE PROTRUSION ON CD0
Ree = T R Re2 3 4 5 6 7 8 9 2 3 4 5 6 7 8 9104 105 106
0.6
0.8
1.0
1.2
1.4
1.6
0.6
0.8
1.0
1.2
1.4
0.4
0.6
0.8
1.0
1.2
1.4
CD0
CD0
CD0
o
o
o
6590
30
65
90
30
65
90
15, 30
dD
= 0.06
dD
= 0.03
dD
= 0.005
The uppmaximuFor othe
Applicability : Uncertainty : R
R
3Ex
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Observe Copyright.
43
ESDU
800252 3 4 5 6 7 8 9 107
dD
0.005
0.03
0.06
D : See Sketch 5.2 ; < 0.05 x 10
-3
Solid lines 10% Dashed lines 15%FIGURE 9 EFFECT OF SINGLE
SPANWISE PROTRUSION ON CL0max
Ree = T R Re2 3 4 5 6 7 8 9 2 3 4 5 6 7 8 9104 105 106
-1.6
-1.2
-0.8
-0.4
0.0
0.4
0.8
CL0 max
See Figure 10 for values of giving CL0 maxand for CL0 at other
values of
0.005 d/D 0.06
ApplicabilityUncertainty :
Location of protrusion of height dCL0 (positive as shown)
V
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.ESDU 80025
FIGURE 10 TYPICAL VARIATIONS OF CD0 AND CL0 WITH FOR CYLINDER
WITH SPANWISE PROTRUSION(S)
0 50 100 150 200
CL0CL0 max
0.0
0.5
1.0
0 50 100 150
CD0 - [CD0]d=0
0.0
0.5
1.0
1.5
0 50 100 150 200CL0
-0.5
0.0
0.5
(a) Subcritical drag coefficientRee . 2 H 105
0 50 100 150 200
CD0
0.5
1.0
1.50.06
0.06
0.03
0.005
dD
dD
0.005
0.03
0.06
0.06
dD
0.005
0.03
0.06
0.06
dD
0.005
0.03
0.06
0.06
CL0 max = 0.8
(b) Subcritical lift coefficientRee . 2 H 104 to approx. 3 H
105
(c) Supercritical drag coefficientRee > 10
6
(d) Supercritical lift coefficientRee > 10
6
Single protrusion
Two plate-type protrusions180 apart
d/D = 0.06 only
44
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ESDU product issue: 2007-01. For current status, contact ESDU.
Observe Copyright.
ESDU
80025NG ON A PLANE SURFACE2 3 4 5 6 7 8 9 107
ability : 2-dimensional cylinderainty : 15% unless otherwise
indicated
Vz
CL0CD0
V
45
FIGURE 11 DRAG AND LIFT COEFFICIENTS FOR A CIRCULAR CYLINDRICAL
SECTION RESTI
Reeff
2 3 4 5 6 7 8 9 2 3 4 5 6 7 8 9104 105 106
(CL0)h=0(based on Veff)
0.4
0.6
0.8
1.0
1.2
1.4
1.6
0.4
0.6
0.8
1.0
1.2
1.4
(CD0)h=0(based on Veff)
Scatter band in critical region
< 0.1
8
20
/ D H 103
8 - 20
< 0.1
/ D H 103
ApplicUncert
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FIGURE 12 VARIATION OF DRAG AND LIFT COEFFICIENTS FOR A CIRCULAR
CYLINDRICAL SECTION NEAR A PLANE SURFACE
h / D
0 1 2 3 4
(CL0)h (CL0)h=0
0.0
0.2
0.4
0.6
0.8
1.0
Data less certain
h / D
0 1 2 3 4
(CD0)h (CD0)h=0(CD0)h=4 (CD0)h=0
0.0
0.2
0.4
0.6
0.8
1.0
1.2
(CL0)h
(CD0)h
h46
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FIGURE 13 PRESSURE DISTRIBUTION CHARACTERISTICS BASE AND
SEPARATION REGIONS
b70 80 90 100 110 120 130 140 150 160
-Cpb
0.2
0.4
0.6
0.8
1.0
1.2
1.4
log Ree
(b) b
DA B
A,B
CDo
Smoothcylinder
Ree ReeBRee ReeA
ReeA < Ree < ReeB(see Appendix C)
CD0
0.0 0.2 0.4 0.6 0.8 1.0 1.2 1.4
-Cpb
0.0
0.2
0.4
0.6
0.8
1.0
1.2
1.4
Cpb
b
Cp1
0
-1
-2
(a) Cpb
Extrapolated data
Uncertainty : 10% in Cpb 5% in bEqn. to curves : See Appendix
C47
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FIGURE 14 PRESSURE DISTRIBUTION CHARACTERISTICS MINIMUM PRESSURE
REGIONb - m
0 10 20 30 40 50 60 70
Cpb - Cpm
0
1
2
3
(b) Cpm
m60 70 80 90 100
b
80
90
100
110
120
130
140
150
Cpb
m b
Cpm
Cp
Extrapolated data
Uncertainty : 4 in m 10% in CpmEqns to curves : See Appendix
C
(a) m
-2
-1
0
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.ESDU 80025
FIGURE 15 LOCAL VELOCITIES AND THEIR RESULTANT DIRECTION IN FLOW
FIELD AROUND A
rD
0.5 1.0 1.5 2.0 2.5 3.0 3.5 4.0
Vs V(r;)Vs V
0.0
0.2
0.4
0.6
0.8
1.0
All values of < b
(a) Local velocities
rD
0.5 1.0 1.5 2.0 2.5 3.0 3.5 4.0
s (r;)s
0.0
0.2
0.4
0.6
0.8
1.090 to 105
15 and 115
30
50 to 90
(b) Local flow angles
s = 90 -
V
(r;) V(r;)r49
CIRCULAR CYLINDER
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.ESDU 80025APPENDIX A GENERAL FEATURES OF THE FLOW AROUND A
CIRCULAR CYLINDER
A1. CYLINDER WITH TWO-DIMENSIONAL FLOW
At very low Reynolds numbers the flow is entirely laminar and
remains attached to the cylindersurface (Sketch A1.1). At
approximately Re = 5 or 6 the flow separates from the rear of the
cylinder anda pair of attached eddies fo