How to measure
turbulence with hot-wireanemometers- a practical guide

Finn E. Jørgensen - 2005

This guide may not be copied, photocopied, translated, modified or reduced to any
electronic medium or machine-readable form, in whole, or in part, without the priorwritten consent of Dantec Dynamics A/S.
Publication no.: 9040U6154. Date 2005-08-30. First edition printed in 2001. © Dantec
Dynamics A/S, P.O. Box 121, Tonsbakken 16-18, DK-2740 Skovlunde, Denmark. All
rights reserved.

2

INTRODUCTION
Turbulence is an important process in most fluid flows and contributes
significantly to the transport of momentum, heat and mass. Turbulence also plays a rolein the generation of fluid friction losses and fluid induced noise. In order to understandthe behaviour of fluid flows and in order to design and evaluate vehicles, engines,
pumps etc. the study of turbulence is therefore essential. Such studies are carried out bymeans of suitable instrumentation like hot-wire anemometers (often called CTA orconstant temperature anemometers with reference to the operating principle) or laserDoppler anemometers (LDA) and more recently with particle-imaging velocimetry(PIV). Measurements are often made as supplement to computer modelling (CFD,
computational fluid dynamics).
The CTA anemometer works on the basis of convective heat transfer from aheated sensor to the surrounding fluid, the heat transfer being primarily related to thefluid velocity. By using very fine wire sensors placed in the fluid and electronics with
servo-loop technique, it is possible to measure velocity fluctuations of fine scales and ofhigh frequencies. The advantages of the CTA over other flow measuring principles areease-of-use, the output is an analogue voltage, which means that no information is lost,and very high temporal resolution, which makes the CTA ideal for measuring spectra.
And finally the CTA is more affordable than LDA or PIV systems.
The booklet is intended to give the reader what he needs to know in order to selectand set up a CTA system and to perform measurements of basic turbulent quantities. It
goes through all the steps needed in order to carry out reliable measurements startingwith a chapter on selection of equipment (anemometer, probes, A/D board etc.)
followed by experiment planning, system configuration and installation, anemometer
setup, velocity and directional calibration, data acquisition and data reduction. The more
knowledgeable reader may only read the text boxes, which are written ascomprehensive step-by-step procedures, and skip the text in-between.
Disturbing effects that may influence CTA measurments are mentioned briefly,
and finally an example on how to calculate the uncertainty of velocities measured with a
CTA anemometer is given. The booklet has a short introduction on the basic theory of
the CTA anemometer.
Two appendices give examples on how to setup and acquire data with the Dantec
MiniCTA and StreamLine anemometers utilizing the Dantec application software.

3

1.

SELECTING MEASUREMENT EQUIPMENT ........................................................................... 6
1.1 MEASURING CHAIN .......................................................................................................................... 6
1.2 PROBE SELECTION............................................................................................................................ 6
1.2.1 Quick guide to probe selection............................................................................................... 7
1.2.2 Sensor types............................................................................................................................ 8
1.2.3 Sensor arrays ......................................................................................................................... 9
1.3 CTA ANEMOMETER/SIGNAL CONDITIONER ................................................................................... 10
1.3.1 Anemometer selection .......................................................................................................... 10
1.3.2 Signal conditioner ................................................................................................................ 11
1.4 A/D BOARD ................................................................................................................................... 11
1.5 COMPUTER .................................................................................................................................... 12
1.6 CTA APPLICATION SOFTWARE ....................................................................................................... 12
1.7 TRAVERSE SYSTEM ........................................................................................................................ 13
1.8 CALIBRATION SYSTEM ................................................................................................................... 13

2.

PLANNING AN EXPERIMENT ................................................................................................... 14

3.

EXPERIMENT STEP BY STEP PROCEDURE ......................................................................... 15

4.

SYSTEM CONFIGURATION....................................................................................................... 16
4.1 PROBE MOUNTING AND CABLING ................................................................................................... 16
4.1.1 Probe mounting and orientation .......................................................................................... 16
4.1.2 Cabling................................................................................................................................. 17
4.1.3 Liquid grounding.................................................................................................................. 17
4.2 CTA CONFIGURATION ................................................................................................................... 18
4.2.1 CTA bridge ........................................................................................................................... 18
4.2.2 Connecting CTA output to A/D board input channels.......................................................... 18
4.3 TRAVERSE SYSTEM........................................................................................................................ 19

5.

ANEMOMETER SETUP ............................................................................................................... 19
5.1 CTA HARDWARE SETUP................................................................................................................. 19
5.1.1 Overheat adjustment ............................................................................................................ 19
5.1.2 How to use overheat adjustment .......................................................................................... 20
5.1.3 Square wave test................................................................................................................... 21
5.2 SIGNAL CONDITIONER SETUP ......................................................................................................... 22
5.2.1 Low-pass filtering................................................................................................................. 22
5.2.2 High-pass filtering ............................................................................................................... 22
5.2.3 Applying DC-offset and Gain ............................................................................................... 23

6.

VELOCITY CALIBRATION, CURVE FITTING ...................................................................... 24

7.

DIRECTIONAL CALIBRATION................................................................................................. 26
7.1.1
7.1.2

8.

X-array probes ..................................................................................................................... 26
Tri-axial probes.................................................................................................................... 27

DATA CONVERSION.................................................................................................................... 28
8.1.1
8.1.2
8.1.3
8.1.4
8.1.5

Re-scaling: ........................................................................................................................... 28
Temperature correction: ...................................................................................................... 29
Conversion into calibration velocities (linearisation).......................................................... 29
X-probe decomposition into velocity components U and V.................................................. 30
Tri-axial probe decomposition into velocity components U, V and W ................................. 31

9.

DATA ACQUISITION ................................................................................................................... 32

10.

DATA ANALYSIS ...................................................................................................................... 33

4

10.1
10.2
10.3
11.
11.1
11.2
12.

AMPLITUDE DOMAIN DATA ANALYSIS ....................................................................................... 33
TIME-DOMAIN DATA ANALYSIS ................................................................................................. 35
SPECTRAL-DOMAIN DATA ANALYSIS ......................................................................................... 35
RUNNING AN EXPERIMENT................................................................................................. 36
GENERAL PROCEDURE:.............................................................................................................. 36
EXPERIMENTAL PROCEDURE IN NON-ISOTHERMAL FLOWS: ....................................................... 37
DISTURBING EFFECTS .......................................................................................................... 38

12.1
FLOW RELATED EFFECTS: .......................................................................................................... 38
12.1.1
Temperature: ................................................................................................................... 38
12.1.2Pressure:.......................................................................................................................... 38
12.1.3Composition:.................................................................................................................... 39
12.2
SENSOR CONDITIONS. ................................................................................................................ 39
12.2.1
Contamination: ................................................................................................................ 39
12.2.2
Sensor Robustness: .......................................................................................................... 39
12.2.3
Sensor orientation: .......................................................................................................... 39
13.

UNCERTAINTY OF CTA MEASUREMENTS ...................................................................... 40

13.1
UNCERTAINTY OF A VELOCITY SAMPLE..................................................................................... 40
13.1.1
Anemometer:.................................................................................................................... 40
13.1.2
Calibration/conversion:................................................................................................... 41
13.1.3
Data acquisition related uncertainties............................................................................. 41
13.1.4
Uncertainties related to experimental conditions ............................................................ 42
13.1.5Velocity sample uncertainty............................................................................................. 43
13.2
UNCERTAINTY OF REDUCED DATA............................................................................................. 44
14.

ADVANCED TOPICS................................................................................................................ 44

15.

THE CTA ANEMOMETER , BASIC PRINCIPLES.............................................................. 46

15.1
CHARACTERISTICS OF THE HOT-WIRE SENSING ELEMENT, ......................................................... 46
15.1.1
Static characteristics - stationary heat transfer............................................................... 46
15.1.2
Dynamic characteristics, frequency limit. ....................................................................... 47
15.2
MECHANICAL DESIGN OF HOT-WIRE PROBES ............................................................................. 49
15.3
SPATIAL RESOLUTION OF HOT-WIRES. ....................................................................................... 49
15.4
DIRECTIONAL SENSITIVITY OF HOT-WIRES. ............................................................................... 49
15.5
THE CONSTANT TEMPERATURE ANEMOMETER......................................................................... 51
16.

REFERENCES............................................................................................................................ 53

5

1.

SELECTING MEASUREMENT EQUIPMENT

1.1

Measuring chain

Fig. 1. Typical CTA measuring chain.
The measuring equipment constitutes a measuring chain. It consists typically of aProbe with Probe support and Cabling, a CTA anemometer, a Signal Conditioner, an
A/D Converter, and a Computer. Very often a dedicated Application soft-ware for CTA
setup, data acquisition and data analysis is part of the CTA anemometer. A traverse
system may be added for probe traverse, when profiles have to be investigated. A
dedicated probe calibrator may speed up an experiment and reduce the total costs, as it
cuts down expensive wind-tunnel time.

1.2

Probe selection
Probes are primarily selected on basis of:·

Fluid medium·

Number of velocity components to be measured (1-, 2- or 3)·

Expected velocity range·

Quantity to be measured (velocity, wall shear strees etc.)·

Required spatial resolution·

Turbulence intensity and fluctuation frequency in the flow·

Temperature variations·

Contamination risk·

Available space around the measuring point (free flow, boundary layer flows,
confined flows).

6

1.2.1 Quick guide to probe selection
Free and Confined Flows
Type of flow
1-Dimensional
Uni-directional

MediumRecommended Probes

Gas

Single sensor Wire
Single sensor Fiber, thin coat.
Wedge-shaped Film, thin coat.
Conical Film, thin coat.
Single sensor Fiber, heavy coat.
Wedge-shaped Film, heavy coat.
Conical Film, heavy coat.
Split-fibers, thin coat.
Split-fibers, heavy coat.

LiquidBi-directional
2-Dimensional
One Quadrant

Gas
LiquidGas
Liquids

Half Plane
Full Plane

Gas
Liquids
Gas
Liquids

3-Dimensional
One Octant(70° Cone)

90° Cone
Full Space
Wall Flows(Shear Stress)
Type of flow
1-Dimensional
UnidirectionalGas

X-array Wires
X-array Fibers, thin coat.
V-wedge Film, thin coat.
X-array Fibers, heavy coat.
V-wedge Film, heavy coat.
Split-fibers, thin coat.
Split-fibers, heavy coat.
Triple-split Fibers, thin coat.
X-array Wire, flying hot-wire
Triple-split Fibers, special

Liquids
Gas
Liquids
Gas

Tri-axial Wire
Tri-axial Fiber, thin coat.
Tri-axial Fiber, Special
Slanted Wire, rotated probe
Slanted Fiber, heavy coat.
Omnidirectional Film

MediumRecommended Probes

Gas

Flush-mounting Film, thin coat.
Glue-on Film, thin coat.
Flush-mounting Film, heavy coat.
Glue-on Film, special

Liquids

7

1.2.2 Sensor types

Anemometer probes are available with four types of sensors: Miniature wires,
Gold-plated wires, Fibre-film or Film-sensors. Wires are normally 5 mm in diameter and1.2 mm long suspended between two needle-shaped prongs. Gold-plated wires have thesame active length but are copper- and gold-plated at the ends to a total length of 3 mmlong in order to minimise prong interference. Fibre-sensors are quartz-fibers, normally
70 mm in diameter and with 1.2 mm active length, covered by a nickel thin-film, which
again is protected by a quartz coating. Fibre-sensors are mounted on prongs in the samearrays as are wires. Film sensors consist of nickel thin-films deposited on the tip of
aerodynamically shaped bodies, wedges or cones.
Sensor type selection:
Wire sensors:
Miniature wires:First choice for applications in air flows with turbulence intensities up to 5-10%.
They have the highest frequency response. They can be repaired and are the mostaffordable sensor type.
Gold-plated wires:
For applications in air flows with turbulence intensities up to 20-25%. Frequency
response is inferior to miniature wires. They can be repaired.
Fibre-film sensors:
Thin-quartz coating:
For applications in air. Frequency response is inferior to wires. They are morerugged than wire sensors and can be used in less clean air. They can be repaired.
Heavy-quartz coating:
For applications in water. They can be repaired.
Film-sensors:
Thin-quartz coating:
For applications in air at moderate-to-low fluctuation frequencies. They are themost rugged CTA probe type and can be used in less clean air than fibre-sensors.
They normally cannot be repaired.
Heavy-quartz coating:
For applications in water. They are more rugged than fibre-sensors. They cannot
normally be repaired.

Note: Wire probes and fibre-film probes with thin quartz coating can be used in nonconducting liquids.

8

1.2.3 Sensor arrays

Probes are available in one-, two- and three-dimensional versions as single-, dual
and triple-sensor probes referring to the number of sensors. Since the sensors (wires orfibre-films) respond to both magnitude and direction of the velocity vector, information
about both can be obtained, only when two or more sensors are placed under different
angles to the flow vector.
Split-fibre and triple-split fibre probes are special designs, where two or three
thin-film sensors are placed in parallel on the surface of a quartz cylinder. They may
supplement X-probes in two-dimensional flows, when the flow vector exceeds an angleof ±45°. They are not supported by commercially available CTA software.
Sensor array selection:

Single-sensor normal probes:
For one-dimensional, uni-directional flows. They are available with different
prong geometry, which allows the probe to be mounted correctly with the sensor
perpendicular and prongs parallel with the flow.
Single-sensor slanted probes (45° between sensor and probe axis):
For three-dimensional stationary flows where the velocity vector stays within acone of 90°. Spatial resolution 0.8x0.8x0.8 mm (standard probe). Must be
rotated during measurement.
Dual-sensor probes:
X-probes:

For two-dimensional flows, where the velocity vector stays within ±45° withrespect to the probe axis.
Split-fibre probes:

For two-dimensional flows, where the velocity vector stays within ±90° withrespect to the probe axis. The cross-wise spatial resolution is 0.2 mm, whichmakes them better than X-probes in shear layers.
Triple-sensor probes:
Tri-axial probes:

For two-dimensional flows, where the velocity vector stays inside a cone of 70°
opening angle around the probe axis, corresponding to a turbulence intensity of
15%. The spatial resolution is defined by a sphere of 1.3 mm diameter.
Triple-split film probes:

For fully reversing two-dimensional flows, Acceptance angle is ±180°.
9

1.3

CTA Anemometer/Signal conditioner

1.3.1 Anemometer selection
Often a CTA anemometer is on hand for an experiment, while it is more seldomthat selecting and purchasing an anemometer is part of the experimental planning. In
both cases, however, it is important to make sure that the anemometer to be used has therequired bandwidth and sufficiently low noise and drift to provide stable and reliable
results. In water applications it is also important to check that the CTA bridge candeliver sufficient power to operate the probe at the expected flow velocity.
CTA anemometer and bridge selection:
Research type CTA:
Bandwidth is typically 100-250 kHz, max. 400 kHz.
Noise contributes typically with 0.005% to a background turbulence of 0.1% of 10
kHz bandwith.
Drift typically 0.5 mV per °C.
CTA bridges:
1:20 General purpose bridge for air applications at bandwidths below approx. 250 kHz.
1:20 General purpose bridge with high power for water applications.
1:1 Symmetrical bridge for bandwidths up to 400 kHz, or for long probe cables up to
100 m (reduces max. bandwidths to typically 50 kHz).
Setup:
Automatic setup of and operation of CTA bridge via application software.
Dedicated type CTA:
Bandwidth is typically 10 kHz.
Noise on output signal is typically 1-2 mV.
Drift typically 0.5 mV per °C.
CTA bridges:
1:20 General purpose bridge for air applications at a bandwidth up to approx. 10 kHz.
Setup:
Manual setup and operation of CTA bridge.

Research type anemometers are normally multi-channel systems with up to 6 ormore CTA channels. They have built-in Signal conditioners for amplification andfiltering of the CTA signal before A/D conversion.
Dedicated anemometers are single-channel instruments supporting only one
sensor. They do normally only have a low-pass filter for the output signal. They can be
combined for multi-point measurements.

101.3.2 Signal conditioner
Most CTA anemometers have built-in Signal Conditioners for high-pass and low-passfiltering and for amplification of the CTA signal.
Signal conditioner selection:
Offset:Should ideally cover the input range of the A/D board. In practice, however, itsuffices to cover the expected range of the CTA output signal, e.g. 0-5 Volts.
Gain:
Improves A/D board resolution. A gain of 16 gives a 12-bit A/D board the same
resolution as a 16-bit board.
High-pass filter:
Removes the DC-part of the signal. Is only needed, when low frequency fluctuations
have to be removed from the signal prior to spectral analysis.
Low pass filter:
Removes electronic noise from the signal and prevents folding back of spectra(aliasing). The filter should be as steep as possible. Research anemometers normally
have a –60dB/decade roll-off, while dedicated simpler anemometers may have –20
dB/decade.

1.4

A/D board

The CTA signal is acquired via an A/D converter board and saved as data-series
in a computer.
Selecting the A/D board:
Number of channels:
Shall as a minimum equal the number of CTA channels plus additional channels (e.g.
temperature) needed in the experiment.
Input range:
Shall cover as a minimum the CTA voltage range. A 0-10 Volts range is well suitedfor most anemometers and applications.
Input resolution:
Shall be sufficient to provide the required resolution in converted data. A 12-bit board
typically gives a velocity resolution of 0.1 to 0.2%.
Sampling rate SR:
Shall be minimum two times the maximum frequency in the flow: SR=2·fmax
SR is reduced by the number of channels, n, in use: SR(n)=1/n·2·fmax
A 100 kHz board covers most low-to-medium velocity applications (<100 m/s).
Simultaneous sampling:
May be needed when correlation between fast sampled multiple channels (e.g.
Reynolds shear stress) is required.
Check the sampling rate per channel, as it may be significantly reduced due to delays
on the board as compared with the sampling rate for consecutively sampled signals
with the same board.
External triggering:
Needed to start the data acquisition by an event related to the flow.

11

1.5

Computer

The choice of computer to be used for CTA measurements is normally not critical.
Speed and memory storage are normally more than sufficient for most applications. It
is, however, important to ensure that the CTA controller, the A/D board driver and thetraverse driver are compatible, i.e. runs under the same operative system and can becalled from the same application software. Also that the required number of com ports
for communication with the CTA anemometer and the traverse system is available.

1.6

CTA application software

Commercially available CTA anemometers are normally delivered together with anapplication software. Advanced software packages control the anemometer and carryout automatic setup of both CTA bridge and signal conditioner [14]. They also perform
automatic velocity and directional calibrations and they can be programmed to perform
automatic experiments with probe traversing and data equisition. Finally data areconverted into engineering units and reduced to relevant statistical quantities: moments,
spectra etc. Application software for manually operated anemometers is also available.
Except for the anemometer and calibrator drivers, they have by and large the samefunctionality as the advanced packages.

Note: It is highly recommended to use professional CTA application software when at all
possible in order to reduce the time and costs it otherwise takes to start up. In special cases,
where the CTA is part of a large measurement system with input from many other types of
instruments including the control of windtunnels and traverses, it may be worthwhileconsidering writing ones own software. Even then, it may be sensible to use the velocity anddirectional calibration routines offered by a professional application software.
12

1.7

Traverse system

A traverse system is needed, if probe movement is part of the experimental procedure. It
may have up to three axis and a rotation unit, if used for slanting probes.
Traverse selection:
Axis:
Number and range of traverse axis shall fit to the experiment.
Resolution:
Linear resolution shall be sufficient. Commercially available traverses for CTA probes
normally have a resolution better than 0.01 mm and can be repositioned withinapprox. ±0.1 mm.
Control:
Automatic traverse is most conveniently controlled from the CTA application software.
Impact on flow pattern:
The traverse should not disturb the flow at the probe position. This may be achieved byusing aerodynamically shaped probe mounts on the traverse.

The traverse should be rigid so that the parts exposed to the wind load do not vibrate or
bend. Such vibrations or bending will bias the velocity measurement.

1.8

Calibration system

A calibration system is normally not considered part of the measuring chain. It plays,
however, an important role for the accuracy and the speed, with which an experimentcan be carried out. Calibrations may be performed in a dedicated calibrator with a lowturbulent free jet, whose velocity is calculated on basis of the pressure drop over its exit.
Calibrations can also be performed in the wind-tunnel, where the experiments are goingto take place, with a pitot-static tube as the velocity reference.
Calibration facility:
Dedicated probe calibrator:
Velocity range. From a few cm/s to several 100 m/s.
Accuracy: Typically ±0.5% of reading above 5m /s.
Additional features: May be used for directional calibration of multi-sensor probes.
Wind-tunnel with Pitot-static tube:
Velocity range: From approx. 2 m/s to typically 50 m/s
Accuracy: Typically ±1% of reading above 5 m/s. Depends on pressure device anddecreases at low velocities.

13

2.

PLANNING AN EXPERIMENTThe quality of fluid dynamic measurements and the efficiency of the experimental
procedure very much depends on the selection of the equipment, inclusive theapplication software, and on the planning of the experiment. Qualified decisions dependon the capability to identify the measurable quantities and to select the data analyses
needed to provide the required results.
What to do:

Check list:

Know what you want to measure, the physicalvariable, the statistical functions, theultimate presentation.

Define quantities to be measured:- Higher order moments (mean, standard
deviation, turbulence, shear stress, etc.).
- Frequency distribution (spectra)- Eddy sizes (length scales)

Know your sensor: sensitivity limitations,potential problems.
Know the results beforehand. If you do notguess, cross check, explore.

Define distribution of measuring points:- Single point measurement- Profiles (probe traverse)- Simultaneously in many points

Design the measurement.
Estimate optimum data rate, measurement
time, number of samples needed.
Check the function of equipment by varying
parameters. Is the system immune to smallchanges in bandwidth, range, gain ….
Monitor the results online – things maychange: temperature, conditions during a
traverse.
Do not leave and go for coffee!

Select Equipment and software on basis of:- Flow medium: Gas or liquid.
- Dimensions: 1-, 2- or 3-dimensional.
- Fluctuations: Turbulence intensity, lengthscales, frequency distribution.
- Temperature: Constant or varying.
- Quantity to be measured: Velocity
components, shear stress, temperatureetc.
Define Experiment procedure on basis of:- Type of flow field: Free or internal flows,
wake flow, boundary layer flow,
reversing flow.
- Point distribution: Single-point or
distributed.
- Data analysis: Amplitude-, time- orspectral domain
Define Data analysis on the basis of:- Required result versus measured quantity.
- Equipment setup and data conversion
setup.

Note: Some of the characteristics, e.g. length scales and frequency distribution, may be
unknown prior to an experiment and have to be measured before the final setup of theexperiment.
14

3.

EXPERIMENT STEP BY STEP PROCEDURE

When the flow and parameters of interest are defined and the necessary hardware
is installed and configured (Chapter 1 and 2), the experimental procedure consists of thefollowing steps (numbers in bracket refer to relevant chapters):
HARDWARE SETUP:

1. Adjust overheat ratio (5.1.1).
2. Measure ambient reference temperature, if temperature variations are expected.
3. If need be, check system response with square wave test (5.1.2).
4. Set low-pass filter in Signal Conditioner (5.2.1).
VELOCITY CALIBRATION:

5. Expose the probe to a set of known velocities and determine the transfer
function (6).
DIRECTIONAL CALIBRATION:

6. Only for 2- and 3-D probes, and only if high accuracy is required. Otherwise
use manufacturer’s defaults for yaw and pitch coeffcients (7).
CONVERSION AND DATA REDUCTION:

7. Transfer function provides calibration velocities (8.1.1-8.1.2-8.1.3).
8. Decomposition using yaw and pitch coefficients provides velocity components(8.1.4 - 8.1.5).
9. Data analysis module provides reduced data. (10).
DEFINE EXPERIMENT:

10. Select hardware setup
Option 1: Adjust overheat ratio if temperature changes are expected (11.2).
Option 2: Leave overheat resistor constant (requires temperature correction ofdata, if temperature changes (11.2).
11. Probe movement: Define traverse grid (for measurements in many points)
DEFINE DATA ACQUISITION:

12. Sampling frequency and number of samples (9).
TEST RUN:

13. Place the probe in the flow and acquire data. Check that reduced data (meanvelocity, standard deviation etc.) are as expected.
RUN EXPERIMENT:

14. Move the probe to position, readjust hardware, if need be, and acquire probe
voltages (11).
CONVERT AND REDUCE DATA:

15. Load the data and apply the selected conversion/reduction routine (10).
PRESENTATION OF DATA:

16. Present data in graphs or export them to a report generator.
15

4.

SYSTEM CONFIGURATION

System configuration is the process of mounting and interconnecting the selectedprobes, cables, CTA anemometers, signal conditioners and A/D channels. The
configuration may also include a Traverse system for the probe.

4.1

Probe mounting and cabling

4.1.1 Probe mounting and orientation
The probe is mounted in the flow with the same orientation as it had during calibration.
Preferably with the wire perpendicular to the flow and the prongs parallel with the flow.

Fig. 2. Probe orientation with respect to laboratory coordinate system.
Straight probes are mounted with the probe axis parallel with the dominant velocity
direction. It is recommended that the probe coordinate system (X,Y,Z) coincides with thelaboratory coordinate system (U,V,W).
The probe is mounted in a probe support, which is equipped with a cable and
BNC connector, one for each sensor on the probe. Film probes are equipped with fixedcables and need no supports. Probe bodies and the probe support are designed so that
their outer surfaces are electrically insulated from the electrical circuitry of the probe or
anemometer circuit. They can therefore be mounted directly to any metal part of the test
rig without the risk of ground loops.
It is important to note that the BNC connectors do not make electrical contact with any metalparts of the rig or elsewhere. The BNC connectors represent the signal ground and may
therefore carry ground loops. It is also important that the BNC connectors on dual- or triplesensor supports do not touch each other, as it will influence the floating amplifiers in the CTA.
It is therefore recommended to cover all BNC connectors with a length of plastic tube.

Important: The probe should only be mounted in its support or removed from it,
when the CTA is switched to Stand- by or the power to the CTA is disconnected.
16

4.1.2 Cabling

Fig. 3. Avoiding ground loops and noise pickup.
The distance between the probe and the CTA should be kept as small as possible.
The standard cable length is 4 meters probe cable plus 1 meter support cable, and thiscombination should be used if at all possible in order to obtain maximum bandwidthand in order to avoid picking up more noise than need be. If longer cables are necessary,it is important to follow the lengths recommended by the manufacturer for the actual
CTA bridge (normally 20 or 100 m).
It is recommended to use the BNC-BNC cables delivered together with the CTA by the
manufacturer in order to match the cable-compensating network in the bridge.
If this is not done, the bridge may become unstable and deliver a useless oscillating voltage
output or, in the worst case, burn the sensor.

4.1.3 Liquid grounding
Film probes mounted in liquids may be damaged, if a voltage difference between
the sensor film and the liquid builds up by electric charges in the flowing medium. Ifsuch charge build up occurs, the insulating quartz coating may break down and the thinfilm will be etched away due to electrolysis. The liquid must therefore be grounded tothe anemometer’s signal ground as close to the probe as possible.

Fig. 4. Grounding of liquid to Signal ground near film probe.

17

4.2

CTA configuration

4.2.1 CTA bridge
The CTA bridge configuration is selected on the basis of the required bandwidth,
the required power to the probe (related to fluid medium, velocity and probe type) andon basis of the distance between probe and the CTA.
Standard CTA bridge:
Bridge ratio 1:20
Resistor in series with the probe: normally 20 ohms.
This bridge configuration can be used in the most applications.
Symmetrical CTA bridge (research type anemometers):
Bridge ratio 1:1
Resistor in series with the probe: normally 20 ohms.
This bridge is recommended for very low turbulence intensities (typically less than0.1%) or very high fluctuation frequencies (typically above 200-300 kHz).
Or when long cables between probe and CTA are needed.
It has lower noise and can be balanced to a higher bandwidth than the 1:20 bridge.
High power CTA bridge (research type anemometers):
Bridge ratio 1:20
Resistor in series with the probe: 10 ohms.
Recommended for high power applications (water at high speeds, e.g. 1 m/s or above).
Probe current is almost doubled (typically 0.8 amps. compared with 0.4-0.5 amps.)

4.2.2 Connecting CTA output to A/D board input channels.

It is important to follow the manufacturer’s instructions when connecting the CTA
output to the A/D board input. Research anemometers where the CTA modules haveseparate power supplies and common signal ground may be connected single-endedreferenced (i.e. with common ground). Dedicated anemometers in separate housingsshould normally be connected differentially in order to avoid cross-talk between
channels. The cable length between the CTA output and the A/D board input should be
kept as short as possible, preferably a few meters. The configuration of the A/D board isdone in the manufacturer’s application software.

18

4.3

Traverse System

The Traverse system is used to move the probe around in the flow. It is selectedon the basis of the number of axis to be traversed, the size of the area to be traversed,
the positioning accuracy and the expected forces from the flow acting on the traverse.
When a PC controlled traverse system is selected, it is important to make sure thatthe moving of the traverse and the acquisition of data can be timed securely. The mostpractical solution is when the traverse can be moved from the CTA application
software, i.e. the traverse is part of the hardware configuration, or when the CTA data
can be acquired in the same software, which controls the traverse. The communication
with the traverse is often done via a serial comport or via a GPIB interface.

5.

ANEMOMETER SETUP

The anemometer setup consists of CTA hardware setup and Signal conditioner
offset and gain adjustment.

5.1

CTA hardware setup

The hardware setup consists of an overheat adjustment (static bridge balancing)
and a square wave test (dynamic balancing). When a signal conditioner is part of the
CTA, the hardware setup also includes low-pass filter and optional gain settings.

5.1.1 Overheat adjustment
The overheat adjustment determines the working temperature of the sensor. The
overheat resistor (decade resistor) in the right bridge arm is adjusted, so that the wanted
sensor operating temperature is established when the bridge is set into Operate. The
cold and warm resistors are related via the overheating ratio, a:

Rw - R0
where Rw is the sensor resistance at operating temperature Tw
R0
and R0 is its resistance at ambient (reference) temperature T0.
a=

The over temperature Tw-T0 can be calculated as:
Tw - To =aa0

where a0 is the sensor temperature coefficient of resistance at T0.

The probe leads resistance and the resistances of the support and cable arenormally provided by the manufacturer and need therefore not to be measured
separately, unless high accuracy in setting the over temperature is required.
Some dedicated CTA anemometers do not have facilities for measuring the probe
cold resistance. In such cases it may suffice to use the resistance values stated on theprobe container.

19

Overheat adjustment procedure:

Measure the total resistance Rtot,0 at ambient temperature T0 and calculate the active
sensor resistance:
R0 = Rtot , 0 - (Rleads + Rsup port + Rcable )Rleads = probe leads resistance, Rsupport = support resistance and Rcable = cable
resistance.
Select a suitable overheat ratio, a.
Recommended values are a= 0.8 in air (over temperature approx 220 °C)
and a=0.1 in water (over temperature approx. 30 °C).

Calculate the decade resistance as:[

Rdec = BR × (1 + a ) × R0 + Rleads + Rsup port + Rcable]

BR= bridge ratio=20 (in most CTA’s)
Adjust the decade resistance to Rdec.
Note: If the probe resistance is measured with an ordinary ohm meter, it isrecommended to check the measuring current. The current should not exceed 1 mA
when measuring the resistance of a 5 mm wire probes in order to avoid heating thewire.

5.1.2 How to use overheat adjustment
The practical use of overheat adjustment depends on how the temperature varies
during setup, calibration and experiment.
The temperature is constant throughout (T varies less than for example ±0.5 °C):
The overheat is adjusted once at the start of the experiment and left untouchedduring calibration and data acquisition (“Automatic overheat adjust” is disabled incomputer controlled anemometers).
The temperature varies from setup to calibration and during the experiment. There
are two options:
1. Overheat adjust. The probe resistance is measured, and the overheat isreadjusted before calibration and before to each data acquistion. The overheat
ratio will then be the same in all situations and the tempearture influence
minimised. (“Automatic overheat adjust” is enabled in computer controlled
anemometers).

20

2. Temperature correction: The overheat is adjusted once and left untouchedduring calibration and data acquisition. The temperature is measured duringcalibration and during the experiment and used to correct the anemometer
voltages before conversion and reduction.
See Chapter 11.2.

5.1.3 Square wave test
The square wave test, or dynamic bridge balancing, serves two purposes: It can beused to optimise the bandwidth of the combined sensor/anemometer circuit or simply tocheck that the servo-loop operates stable and with sufficiently high bandwidth in thespecific application. It is carried out by applying a square wave signal to the bridge top.
The time it takes for the bridge to get into balance is related to the time constant, andhence the bandwidth, of the system. Most CTA anemometers have built-in square-wave
generators. If not, they normally have input for an external square wave generator.
Square wave test procedure:

Expose the probe to the expected maximum velocity.
Connect an oscilloscope to the CTA output, if the square wave is not displayed in theapplication software.
Apply the square wave to the bridge.

Adjust amplifier filter and gain until the response curve gets a 15% undershoot. The
response should be smooth without “ringing” either at the top or at the zero line.
Determine Dt being the time it takes the servo-loop to regulate back to 3% of its
maximum value with an undershoot of 15%.
Calculate the bandwidth of the probe/anemometer system (or cut-off frequency) fc:
fc =1
1.3 × Dt

(wire probes) [10]fc =1(fibre-film probes) [11]Dt

The bandwidth is defined as the frequency, at which the fluctuation amplitude is damped
by a factor 2 (–3 dB limit).
Note: For wire probes up to 100 m/s the amplitude damping starts at frequencies 0.3 0.5 times smaller than the –3 dB cut-off frequency determined by the square wave test.
The response can be optimised by adjusting the amplifier filter and gain. High gain
setting gives high bandwidth, but also greater risk for the servo-loop to become
unstable. It is therefore often recommended to reduce the gain in order to run safely.
21

Most CTA manufacturer’s are recommending default settings for gain and filter, which
can be used in most applications. Dedicated CTA anemometers often have fixed setup
for the servo-loop, which works within the bandwidth stated for them without further
adjustment by the user.

5.2

Signal Conditioner setup

The signal conditioner provides facilities for the filtering and the amplification of
the CTA signal prior to digitizing by the A/D converter.

5.2.1 Low-pass filtering.
Low-pass filtering is used in order to remove noise and to prevent higher
frequencies from folding back (anti-aliasing). The setting of the low-pass filter relates tothe highest frequency in the flow.
Low-pass filtering:
Estimate the highest frequency: fmax.
f cut -off = 2 × f max
Select the cut-off, frequency:
Select the filter setting closest
to the cut-off frequency.

If low-pass filtering is not performed, the energy at frequencies lower than fcut-off
will be contaminated by higher frequencies if the Nyquist sampling criteria is applied.
This appears as a false energy peak in the power spectrum.

5.2.2 High-pass filtering
High-pass filtering is used to clean the signal, if FFT spectra calculation isrequired. When the CTA signal fluctuates on a timescale longer than the total length ofthe data record, it will give unwanted high frequency contributions in an FFT-based
spectrum. Otherwise it should not be applied.
High-pass filtering:
Select the data record length, trecord.
Calculate the high-pass cut-off
frequency: f cut - off =5
2 × t record

This eliminates waves with a wavelength larger than 2/5 of the record length. Shorter waves
will not be interpreted as erroneous non-stationary contributions to the signal.

22

High-pass filtering will make the signal stationary. It should be noted that nospectral information is available below the cut-off frequency of a high-pass filter.
High-pass filters with a sharp and low cut-off frequency are difficult to establish
and they very often have large phase lags. They should therefore be used with care. A
better solution might be to perform digital filtering of the full data set with, for example,
a sixth order filter.

5.2.3 Applying DC-offset and Gain
DC-offset:
The CTA signal level may be reduced by subtraction of a DC-offset voltage. Thisis necessary if the signal moves outside of the range of the A/D board, when a highamplification of the signal is needed prior to digitizing.
DC-offset procedure:
Determine the minimum value Emin of the CTA signal to be measured.
Adjust the DC-offset in the Signal conditioner to: Eoffset = Emin
Note: Avoid applæying DC-offset if possible, as the signal then no longer directly represents
the power transferred from the sensor to the fluid. The usual temperature correction routines
are therefore no longer valid, unless the signal is reconstructed by adding the DC-offset prior
to correction.

Signal amplification (Gain)
The CTA signal may have to be amplified in order to utilise an A/D board with aresolution, that is too small for the application.
In most low to medium velocity applications with a turbulence intensity above 2%
to 3 %, a 12 bit A/D board is sufficient without the need for amplification of the CTA
signal. A 12 bit A/D board has a resolution of 2.4 mVolts in the 0-10 Volts range. By
applying a gain of 16 to the CTA signal prior to digitization the 12-bit resolution is
improved to 0.15 mV corresponding to that of a 16 bit board with CTA gain 1. This issufficient for measurement of background turbulence down to approximately 0.1%.
Gain setting procedure:
Determine the required velocity resolution DU in m/s.
Calculate the mean slope dE/dU of the probe calibration curve in the velocity range ofinterest:

dE E (U 2 ) - E (U 1 )where E(U) is the CTA voltage at the velocity U.
=
dU
U 2 - U1dE
Calculate the required voltage resolution: DE = DU ×dU
DE AD
Calculate the gain G as: G =where DEAD is the resolution of the A/D board.
DE

23

6.

VELOCITY CALIBRATION, CURVE FITTING

Calibration establishes a relation between the CTA output and the flow velocity. Itis performed by exposing the probe to a set of known velocities, U, and then record thevoltages, E. A curve fit through the points (E,U) represents the transfer function to be
used when converting data records from voltages into velocities. Calibration may either
be carried out in a dedicated probe calibrator, which normally is a free jet, or in a windtunnel with for example a pitot-static tube as the velocity reference. It is important tokeep track of the temperature during calibration. If it varies from calibration tomeasurement, it may be necessary to correct the CTA data records for temperature
variations.
Velocity calibration procedure:

Mount the probe in the calibration rig with the same wire-prong orientation as will be
used during the experiment.
- Single-sensor probes: with the prongs parallel with the flow.
- X-probes and Tri-axial probes: with the probe axis parallel with the flow.
Record the ambient conditions: Temperature, Ta , and barometric pressure, Pb.
Setting to operate:1) Calibration with temperature correction:
Switch the anemometer to Operate with the previously established overheat setup.
2) Calibration with overheat adjustment:
Balance the bridge immediately before calibration and establish a new overheat
setup using the same overheat ratio a.
Choose min. and max. calibration velocity, Umin,cal and Umax,cal ,Choose number of calibration points (a minimum of 10 points is recommended).
Choose velocity distribution (logarithmic distribution is recommended).
Create the velocities and acquire the CTA voltage together with velocity and ambient
temperature in all points.
Research type anemometers may be delivered with automatic calibrators andcalibration routines in their application software, thus offering fully automatic
calibrations inclusive of curve fitting.

24

CTA application software packages contain curve fitting procedures, whichcorrect the voltages and calculates the transfer functions on basis of advanced curve
fitting methods eliminating the need for any data manipulations by the user.
Curve fitting of calibration data (manual procedure):

Arrange the probe data in a table, for example in Excel, containing velocity U, CTA voltage E,
fluid temperature Ta and pressure Pb.
Correct the voltages E for temperature variations during calibration, see Chapter 7.1.2.
Polynomial curve fitting:
Plot U as function of Ecorr
Create a polynomial trend line in 4th order:
2

3

4

U = C 0 + C1 Ecorr + C 2 E coor + C 3 E corr + C 4 E corr , Co to C4 are calibration constants.
The polynomial curve fit is normally recommended, as it makes very good fits withlinearisation errors often less than 1%.
Note: Polynomial curve fits may oscillate, if the velocity is outside the calibration velocity
range.
Power law curve fitting:
Plot E2 as function of Un in double logarithmic scale (n=0.45 is a good starting value forwire probes).
Create a linear trend line. This will give the calibration constants A and B in the function:

E 2 = A + B × U n (King’s law [15])Vary n and repeat the trend line until the curve fit errors are acceptable.
Power law curve fits are less accurate than polynomial fits, especially over wide velocity
ranges, as n is slightly velocity dependent.
Velocity calibration of X-probes and Tri-axial probes:

The calibration velocity range must be expanded with respect to the velocity limits
expected during the experiment thus making sure that the curve fit is valid over thefull angular acceptance range of the probes. Umin,exp and Umax,exp are peak values.
Umin,calUmax,calX-probes

0.1· Umin,exp

1.5· Umax,exp

Tri-axial probes

0.15· Umin,exp

1.6· Umax,exp
25

7.

DIRECTIONAL CALIBRATION

Directional calibration of multi-sensor probes provides the individual directional
sensitivity coefficients (yaw factor k and pitch-factor h) for the sensors, which are used
to decompose calibration velocities into velocity components.
Note: In many situations, where optimal accuracy is not needed, the manufacturer’s default
values for k and h can be used, eliminating the need for individual directional calibration.

7.1.1 X-array probes
The yaw coefficients, k1 and k2, are used in order to decompose the calibration
velocities Ucal1 and Ucal2 from an X-probe into the U and V components.
Directional calibration of X-probes requires a rotation unit, where the probe can berotated on an axis through the crossing point of the wires perpendicular to the wire
plane. Calculation of the yaw coefficients requires that a probe coordinate system isdefined with respect to the wires (see the sketch below), and that the probe has beencalibrated against velocity.
X-probe calibration procedure:

Define probe coordinate system (X,Y) with respect to wire 1 and 2 as shown below:

Mount the probe in the rotating holder oriented as shown above.
Estimate the maximum angle amax , which is expected in the experiment between thevelocity vector Ua and the probe axis. In most cases amax is selected to =40°.
Select the number of angular positions for the calibration.
Expose the probe to the middle calibration velocity Udir,cal = 1/2·(Umin,cal+Umax,cal)
Rotate the probe to the -amax position and acquire the voltages E1 and E2 from the two
sensors.
Check that E1 is bigger than E2 and that E1 increases, while E2 decreases, when the probe
is moved to next angular position. If not turn the probe180° around its X-axis and startagain.
Read E1 and E2 in each angular position.
2
2
Calculatethe squared
yaw factor ksoftware
for sensor
1 androutines
sensor 2forin eachposition
Advanced
CTA application
containautomatic
1 and k2packages
Chapter
8.1.4. of the yaw coefficients.
using the equationsin anddirectional
calibration
evaluation

Calculate the average of the k12 and k22 ,respectively, factors and use them as sensitivity
factors for the two sensors.
26

7.1.2 Tri-axial probes
The directional sensitivity of tri-axial probes is characterised by both a yaw and apitch coefficient, k and h, for each sensor. Calibration of tri-axial probes requires aholder, where the probe axis (X-direction) can be tilted with respect to the flow andthereafter rotated 360° around its axis. Proper evaluation of the coefficient requires thata probe coordinate system is defined with respect to the sensor-orientation. Directional
calibration is made on the basis of a velocity calibration.
Tri-axial probe calibration procedure:

Define a probe coordinate system (normally use the manufacturer’s suggestion):

Mount the probe in the rotating holder with the probe axis in the flow direction and wire
no. 3 in the XZ plane of the calibration unit system, corresponding to a=0.
Estimate the maximum angle bmax , which is expected in the experiment between thevelocity vector and the probe axis. In most cases bmax is selected to 30°.
Select the number of angular positions a for the calibration, normally 24 corresponding to
15° steps.
Expose the probe to the mid calibration velocity range Udir,cal = 1/2·(Umin,cal+Umax,cal) andacquire the voltages E1 , E2 and E3 from the three sensors.
Tilt the probe to the bmax position with a=0 and acquire E1 , E2 and E3.
Rotate the probe and acquire E1 , E2 and E3 in all a-positions.
Calculate the squared yaw factor k12 , k22 and k32 and pitch factors for sensor 1 , 2 and 3 ineach position using the equations in the Theoretical part, chapter YY.
Calculate the average of the k2- and h2-factors and use them as sensitivity factors for thethree sensors.

Note: Directional calibration normally only needs to be carried out once in a probe’s
lifetime, as it depends only on the geometry, which will not change in use.

27

8.

DATA CONVERSION

It is advised to define the data conversion prior to running the experiment. Data
conversion transforms the CTA voltages into calibration velocities in m/s by means of
the calibration transfer function. Multi-sensor probes are furthermore decomposed into
velocity components in the probe coordinate system. If it differs from the laboratory
coordinate system, the velocity components are finally transformed into the laboratory
coordinate system.
Data conversion consists of the following processes:

1. Re-scaling of acquired CTA
output voltages (raw data)

Only if Signal Conditioner gain and offset havebeen applied.

2. Temperature correction

Only if sensor temperature has been kept constantduring experiment (no overheat adjust).

3. Linearisation

Only if data reduction in amplitude domain isrequired.

4. Decomposition into velocity
components

Only for X-probes and Tri-axial probes.

Commercial CTA application software contains modules for data conversion,
where raw data are converted into velocity components according to the scheme above.
Unless special conditions prevail, it is recommended to use such dedicated software
packages.

8.1.1 Re-scaling:
When a CTA signal has been subject to a DC-offset and amplification between
overheat setup and calibration, it has to be re-scaled before it can be linearised.
Re-scaling of CTA-signals:

Calculate the re-scaled voltage E from the acquired voltage Ea:
E=Ea- E offset
Gain

28

8.1.2 Temperature correction:
If the overheat ratio has not been adjusted prior to the data acquisition, the CTA
output voltage must be corrected for possible temperature variations before conversion.
The fluid temperature needs then to be acquired along with the CTA signal.
Temperature correction of CTA voltages:
Acquire the fluid temperature, Ta , together with the CTA voltage, Ea.
Calculate the corrected CTA voltage, Ecorr ,from:æ T - T0 ö÷÷
E corr = çç w
T
T
a ø
è w

0.5

× Ea

[60]

where:
Ea = acquired voltage
Tw = sensor hot temperature = a/a0+T0
T0 = ambient reference temperature related to the last overheat setup before calibration
Ta = ambient temperature during acquisition

This expression can be used for moderate temperature changes in air %±5 °C. The
useful range may be expanded by reducing the exponent n from 0.5 to 0.4 or 0.3.

8.1.3 Conversion into calibration velocities (linearisation)
The CTA voltages are converted into velocities by inserting the acquired voltages
into the calibration transfer functions after re-scaling and temperature correction, if
needed. The simplest and most accurate transfer function is the polynomial, at least in
the case of a wide dynamic velocity range.
The velocities are calculated as if the velocity attacked the probe under the sameangle during measurement as during calibration.
Polynomial linearisation of CTA voltages:
Insert the acquired CTA voltage (after possible corrections) into the polynomial:
Create a polynomial trend line of 4th order:
2

3

U = C 0 + C1 Ecorr + C 2 E coor + C 3 E corr + C 4 E corr

4

where C0 to C4 are the calibration constants.
Note: Do not use the polynomial linearisation function outside the calibration range, as it may
oscillate.

Power law linearisation of CTA voltages:

Insert the acquired CTA voltage (after possible corrections) into the function:1

æ E2 - Aön÷÷
U = ççè B ø

where A, B and n are the calibration constants.
29

8.1.4 X-probe decomposition into velocity components U and V
In 2-D flows measured with X-probes, the calibrated velocities together with theyaw and coefficients k2 are used as intermediate results to calculate the velocity
components U and V in the probe coordinate system.
The yaw coefficients for the two sensors may be the manufacturer’s default
values, or if higher accuracy is required they are determined by directional calibration of
the individual sensor. In simple cases, the coefficients may be neglected.
Decomposition of X-probe voltages into U and V:

Calculate the calibration velocities Ucal1 and Ucal2 using the linearisation functions forsensor 1 and 2.
Decomposition with yaw coefficients k1 and k2 :Calculate the velocities U1 and U2 in the wire-coordinate system (1,2) defined by
the sensors using the two equations:222

k1 × U 1 + U 2 =22

2

U1 + k2 U 2 =

(

)

1
2
2
× 1 + k1 × U cal1
2

(

)

1
2
2
× 1 + k 2 × U cal 22which gives:

(

)

(

)

U1 =

2
2
2
2
2
× 1 + k 2 × U cal 2 - k 2 × U cal1
2

U2 =

2
2
2
2
2
× 1 + k1 × U cal1 - k1 × U cal 2
2

Calculate the velocities U and V in the probe coordinate system (X,Y) from:
U=

2
2
×U1 +
×U 2
2
2

V =

2
2
×U1 ×U 2
2
2

Manufacturer’s (Dantec Dynamics) default values for Yaw-coefficients, k2:

Miniature wire probes:
Gold-plated wire probes:
Fiber-film probes for air:

k12=k220.04
0.02250.04

30

8.1.5 Tri-axial probe decomposition into velocity components U, V and W
In a 3-D flows measured with a Tri-axial probe the calibration velocities are used
together with the yaw and pitch coefficients k2 and h2 to calculate the three velocity
components U, V and W in the probe coordinate system (X,Y,Z).
The yaw and pitch coefficients for the three sensors may be the manufacturer’s
default values, or if higher accuracy is required they are determined by directional
calibration of the individual sensors.
Decomposition of Tri-axial probe voltages into U, V and W:
Calculate the calibration velocities Ucal1 , Ucal2 Ucal3 using the linearisation functions for sensor
1, 2 and 3.

Decomposition with individual yaw and pitch coefficients:
Calculate the velocities U1 , U2 and U3 in the wire-coordinate system (1,2,3) defined by thesensors using the three quations:() × cos 54.74 × U
h × U + k × U + U = (1 + k + h )× cos 54.74 × U
U + h × U + k U = (1 + k + h ) × cos 54.74 × U
2

2

2

2

2

2

k1 × U 1 + U 2 + h1 × U 3 = 1 + k1 + h1
2

2

2

2

1

2

2

1

2

3

2

2

3

2

2

2

2

2

3

2

2

cal1
2

2

2

3

2

2

2

2

2

3

2

cal 2

2

3

2

cal 3

With the k2=0.0225 and , h2=1.04 default values for a tri-axial wire probe, the velocities U1, U2
and U3 in the wire coordinate system becomes:
22

U 1 = - 0.3477 × U cal 1 + 0.3544 × U cal 2 + 0.3266 × U cal 322

U 2 = 0.3266 × U cal 1 - 0.3477U cal 2 + 0.3544 × U cal 3
2

2

2

2

U 3 = 0.3544 × U cal 1 + 0.32663 × U cal 2 - 0.3477 × U cal 3

2

Calculate the U, V and W in the probe coordinate system:

U = U 1 × cos 54.74 + U 2 × cos 54.74 + U 3 × cos 54.74
V = -U 1 × cos 45 - U 2 × cos135 + U 3 × cos 90
W = -U 1 × cos114.09 - U 2 × cos114.09 - U 3 × cos 35.26
Manufacturer’s (Dantec Dynamics) default values for k2 and h2:
Gold-plated wire sensors:
Fiber-film sensors for air:k2
0.0225
0.04

h2
1.04
1.20

31

9.

DATA ACQUISITION

The CTA signal is a continuos analogue voltage. In order to process it digitally it
has to be sampled as a time series consisting of discrete values digitized by an analogueto-digital converter (A/D board).
The parameters defining the data acquisition are the sampling rate SR and thenumber of samples, N. Together they determine the sampling time as T=N/SR. The
values for SR and N depend primarily on the specific experiment, the required data
analysis (time-averaged or spectral analysis), the available computer memory and theacceptable level of uncertainty. Time-averaged analysis, such as mean velocity and rms
of velocity, requires non-correlated samples, which can be achieved when the time
between samples is at least two times larger than the integral time scale of the velocity
fluctuations. Spectral analysis requires the sampling rate to be at least two times thehighest occurring fluctuation frequency in the flow. The number of samples depends on
the required uncertainty and confidence level of the results.
Time avaraged analysis:
Estimate the following expected quantities in the flow:
velocity U [m/s ] , turbulence intensity Tu [ %] , andintegral time-scale T1 [ seconds] (see Chapter 10.2).
Select the wanted uncertainty and confidence level:
uncertainty u, %, in Umean
confidence level (1-a), %Calculate the sampling rate SR:SR £1(gives uncorrelated samples)
2T1

Calculate the number of samples N:öæ1 æ z ö
N = çç × ç a ÷ × Tu ÷÷øèu è 2 ø

za/2
1.65
1.96
2.33

2

(1-a) %
90
95
98

where za/2 is a variable related to confidence level (1-a) of the Gaussian probability density
function p(z).
Sampling rate SR for time spectral analysis:
Calculate the sampling rate SR:

SR ³ 2 × f max (Nyquist critrium with fmax based onan oversampled time series.), or

SR = 2 × f cut -off (based on low-pass filter setup), or
SR = 2.5 × f cut -off (the factor 2.5 adopts to a nonideal low-pass filter, which does not set the signal tozero at the cut-off frequency [57]).

32

10. DATA ANALYSISAs the CTA signal from a turbulent flow will be of random nature, a statisticaldescription of the signal is necessary. The time series can be analysed or reduced either
in the amplitude domain, the time domain or in the frequency domain. The following
procedures all require stationary random data.
CTA application software contains modules that perform the most common data
analysis, as defined below. The standard procedure is to select the wanted analysis andapply it to the actual time series. The reduced data will then be saved in the project andbe ready for graphical presentation or for exporting to a report generator.

10.1 Amplitude domain data analysis
The amplitude domain analysis provides information about the amplitude
distribution in the signal. It is based on one or more time series sampled on the basis ofa single integral time-scale in the flow. A velocity time series represents data from one
sensor, converted into a velocity component in engineering units.
A single velocity time series provides mean, mean square and higher ordermoments.
Moments based on a single time series:
Mean velocity:

U mean =

1 N
åU i
N 1

Standard deviationof velocity:

æ 1 N(U i - U mean )2 ö÷U rms = çå
è N -1 1øTurbulence intensity:

Tu =Skewness:

S =å

Kurtosis (or flatness):

0.5

U rms
U meanN(U i - U mean )3

1

N ×s 3N(U i - U mean )4

1

N ×s 4K =å

where the variance s is defined as:æ N (U i - U mean )2 ö÷
s = çç å
÷
N -1
è 1
ø

0.5

The Skewness is a measure of the lack of statistical symmetry in the flow, while the Kurtosis
is a measure of the amplitude distribution (flatness factor).

33

Two simultaneous velocity time series provide cross-moments (basis for Reynolds
shear stresses) and higher order cross moments (lateral transport quantities), when they
are acquired at the same point. If they are acquired at different points they provide
spatial correlations, which carries information about typical length scales in the flow.
Moments based on two time series:
Reynolds shear stresses:

Lateral transport quantities:

1 N
å (U i - U mean ) × (Vi - Vmean )N 1
1 N
uw = å (U i - U mean ) × (Wi - Wmean )N 1
1 N
vw = å (Vi - Vmean ) × (Wi - Wmean )
N 1
1 N
2
u 2 v = å (U i - U mean ) ×(Vi - Vmean )
N 1
1 N
2
u 2 w = å (U i - U mean ) ×(Wi - Wmean )
N 1
1 N
2
v 2 u = å (Vi - Vmean ) ×(U i - U mean )
N 1
1 N
2
v 2 w = å (Vi - Vmean ) ×(Wi - Wmean )
N 1
1 N
2
w 2 v = å (Wi - Wmean ) ×(Vi - Vmean )
N 1
uv =

34

10.2 Time-domain data analysis
The most often applied time-domain statistic is the auto-correlation function,
Rx(t), from which the integral time-scale can be calculated. This is an important
quantity, as it defines the time interval between statistically uncorrelated samples.
In most CTA application software with data reduction features, the autocorrelation coefficient function is normally calculated and graphically displayed. It
starts with the value 1 at time zero, drops down to zero and normally continues
oscillating around zero. A reasonable estimate of TI is the time it takes the coefficient todrop from the unity start value to zero.
Auto-correlation function and integral time-scale:Requires a long time series x(t) sampled according to the Nyquist criteria.
Auto-correlation function:T1x(t ) ×x(t + t ) × dt
T ®¥ T ò0

R x (t ) = lim¥

Integral time-scale:

TI = ò r x (t ) ×dt
0

where the auto-correlation
coefficient is defined as:r x (t ) =R x (t )R x (0)Note: Auto-correlation can be made on non-linearised raw data.

10.3 Spectral-domain data analysis
Spectral analysis can be used to provide information about how the energy of thesignal is distributed with respect to frequency.

Power spectrum of the flow behind a circular cylinder.
The analysis can be performed on raw, non-linearised signals, provided they aresampled according to the Nyquist criteria. The accuracy of the spectra depends on thealgorithm used and on the number of samples, which normally must be high. There exist
a number of different algorithms for the calculation of spectra mostly based on Fouriertransforms, which produce values of discrete frequencies within sub-records of thesignal. Normally CTA application software contains routines for spectral analysis.
3511. RUNNING AN EXPERIMENTThe experiment can be executed when system setup, probe calibration, dataacquisition setup, and data reduction (algorithms for data analysis) have been
established. Prior to running the experiment it is advised to verify the complete setup by
performing measurements in a known part of the flow. Probe calibrations before andafter the experiment are advisable in order to check probe stability.

11.1 General procedure:
Before the experiment can start, the measuring system must be configured, the CTA
bridge and Signal Conditioner set up and the data acquisition and data reduction
defined in accordance with the flow characteristics.
Running an experiment, general procedure:
Calibrate the probe(s). It is always recommended to calibrate the probe immediately before
and after an experiment.
Verify the setup:
Position the probe in a part of the flow, which is reasonably well known, and acquire
data in one or more points.
Perform data reduction in both amplitude and spectral domain (Umean, Urms andPower spectra as minimum).
Compare with expected values.
Check stability of statistics by comparing results from data records of different
lengths.
Adjust data acquisition setup (sample rate SR and number of samples N), if need be.
Position the probe in the flow together with a temperature probe, if temperature correction ofdata is required.
Move the probe to the proper position in the traverse grid (if employed).
Acquire the CTA output voltages together with other signals needed for correction or control
and move to next position.
Analyse (reduce) data before the experiment is shut down, if possible.
Re-calibrate the probe after the experiment and compare with previous calibration. This canbe done in practice by reducing the same raw data set by means of the two calibrations andcompare the results.
Note: If the calibration drifts linearly with time during
an experiment, the drift may be compensated for byusing a new transfer function based on the averages ofvelocites calculated from identical voltage values
inserted into the transfer functions from the first andthe second
calibrations.Uav=(U1+U2)/2=(fcal1(E1)+fcal2(E1))/2.

36

11.2 Experimental procedure in non-isothermal flows:
As the CTA anemometer is sensitive to variations in ambient temperature, as wellas velocity, it is often necessary to make special precautions in non-isothermal flows inorder to eliminate errors in the measured velocity due to temperature variations. The
error in thevelocity measured with a wire probe in air is approximately 2% per 1 °Cchange in air temperature. The measured velocity decreases with increasing temperatureand vice versa.
This error may be avoided by setting up the CTA bridge and correcting the data in
one of the following ways:
1. Operate the probe with a constant sensor temperature (obtained by leaving thedecade resistor in the CTA fixed during calibration and data acquisition) and correct
the CTA voltage before linearisation and data reduction. The ambient temperaturemust be acquired simultaneously with a temperature sensor, which is fast enough tofollow the temperature variations.
2. Operate the probe with a constant overheat ratio (obtained by adjusting theoverheat ratio before each calibration and data acquisition). This requires that theambient temperature remains constant (or nearly constant) during the time it takes toperform a data acquisition.
CTA setup and Data conversion in non-isothermal flows:
Constant sensor temperature (fixed decade resistance) with temperature correction of data:
Adjust the overheat ratio a at a known ambient temperature Tref.
Leave the CTA bridge and make no more overheat adjustments during the experimentor during recalibrations (disable “automatic overheat adjust” in StreamLine).
Calibrate the probe and measure temperature in each calibration point. Correct the raw
voltages to Tref and make a curve fit.
Position the probe in the test rig and acquire the CTA voltages, Ea ,and ambient
temperature, Ta ,as close to the probe as possible.
Correct the raw CTA voltages (see Chapter 8.1.2) before further conversion(linearisation) and reduction.
Constant overheat ratio without temperature correction of data:
Adjust the overheat ratio, a, at a known ambient temperature Ta.(Enable “Automatic
overheat adjust” in StreamLine).
Calibrate the probe at Ta and make a curve fit.
Position the probe in the test rig and re-adjust the overheat ratio, a, at the new ambient
temperature.
Acquire the CTA voltages E.
Convert (linearise) and reduce the raw CTA voltages without any prior corrections.

37

12. DISTURBING EFFECTS
Measurements with hot-wire anemometers are influenced by a number ofdisturbing effects. In fact any change in a parameter that enters into the mechanism ofheat transfer from the wire to its surroundings may act as a disturbing effect and reduce
the accuracy of the measurement result. The effects may be related to the flow medium
and sensor condition. For special effects from e.g. natural convection, wall nearness etc.
please refer to the CTA literature.

12.1 Flow related effects:
12.1.1 Temperature:
Temperature variations are normally the most important error source, as the heattransfer is directly proportional to the temperature difference between the sensor and thefluid. For a wire probe operated under normal conditions, the error in measured velocity
is approx. 2% per 1 °C change in temperature. For film probes in water the error may be
up to 10% per 1 °C. In both cases the measured velocity decreases with increasing
ambient temperture.
Different precautions can be taken in order to avoid systematic conversion errors
when probe voltages are converted into velocities. One solution is to readjust theoverheat resistor to the changed temperature, so that overheat ratio is kept constant fromcalibration to measurement. Another solution is to leave the overheat resistor constant,measure the temperature and correct the probe voltage. See Chapter 10.2 Experimental
procedure in non-isothermal flows. A special case is the temperature-compensated wireprobe with build-in temperature-sensitive overheat resistor which measures velocity
independent of temperature variations.

12.1.2 Pressure:Pressure variations:

Pressure variations enter directly into the heat transfer equation, as the probe infact measures the mass flux r·U. Normally probes are calibrated against velocity only.
As pressure variations from calibration to experiment and during an experiment arenormally small, the pressure influence in the CTA measurements is normally neglected.

Pressure range:

The lower limit for pressures, at which a probe can be used, are determined by theslip-flow conditions defined by the Knudsen number Kn (ratio between molecular mean
free path and sensor diameter should be smaller than 0.01). For a 5 mm wire probe atatmospheric conditions Kn=0.2. Provided density variations are small the flow is
considered to be a continuum, and pressure effects are normally neglected.

38

12.1.3 Composition:
In most cases the fluid composition remains constant during calibration andexperiment, and it is of no importance. In air one normally experiences variations inwater vapour content (humidity). The influence is very small, less than 1%, and isalmost always neglected.

12.2 Sensor conditions.
12.2.1 Contamination:
Particle contamination reduces the heat transfer resulting in a downward drift in
the calibration. The influence of particle contamination increases with decreasing sensor
surface. Wire probes with 5 µm sensors can be used without problems in normal
laboratory air, if they are recalibrated at regular intervals. Fiber-film probes are lesssusceptible and can be used, e.g. in outdoor applications without problems. If thecalibration drifts significantly, it may be necessary to clean the sensor.
Contamination is a much bigger problem in liquid flows than in gas flows. Thismeans that film probes with non-cylindrical sensors should always be preferred forfiber-film probes whenever possible, unless a careful filtering of the water is carried out.

12.2.2 Sensor Robustness:
Normally all probes will survive almost any experiment, when safely placed in thetest rig. By far the most damages to sensors happen during handling. It is, however,wise to take the robustness of the probe into consideration before it is selected for aparticular application. In general the robustness increases with the size of the sensor.

12.2.3 Sensor orientation:
The effect of sensor orientation is neglectible as long as the sensor is placed
identically with respect to the flow during calibration and measurement. The
misalignement is normally so small that it may be neglecetd as an error source.

3913. UNCERTAINTY OF CTA MEASUREMENTS
Current standards refer to the ISO uncertainty model which combines uncertainty
contributions U(yi) from each individual input variable xi into a total uncertainty at agiven confidence level. The output variable is defined as yi=f(xi).
The relative standard uncertainty u(yi) is a function of the standard deviation of
the input variance:u( yi ) =

æ Dx ö
1× S × çç i ÷÷yi
è ki ø

where S= ∂yi/∂xi is the sensitivity factor and ki is the coverage factor related to the
distribution of the input variance (gaussian, rectangular etc.).
As most engineering applications are assumed to have a Gaussian error
distribution, the 95% confidence level normally required is achieved by multiplying thestandard uncertainty with the coverage factor k=2. The total relative expanded
uncertainty then becomes:
U (tot ) = 2 ×

å u( y )2i

The uncertainty of the results obtained with the CTA anemometer is acombination of the uncertainties of the individually acquired voltages converted into
velocity and the uncertainty of the statistical analysis of the velocity series. The
following chapters provide a guide on how to estimate the uncertainties of CTA
measurements under normal conditions.

13.1 Uncertainty of a velocity sample.
This chapter presents the uncertainty of a single velocity sample acquired via an
A/D from a CTA anemometer with a single-sensor probe. The uncertainty of eachindividual velocity sample is determined by non-statistical means based on detailed
knowledge about the instrumentation, calibration equipment and experimental
conditions. The uncertainties presented below are relative expanded uncertainties.

13.1.1 Anemometer:
Drift, noise, repeatability and frequency response:

Commercially available anemometers have low drift, low noise and good
repeatability so that these factors do not add significantly to the uncertainty incomparison with other error sources. In certain applications, e.g. dissipation
measurements, the high frequency noise of the anemometer may be of importance.
The frequency characteristic of the anemometer will not add to the uncertainty,
when the frequencies in the flow are below approximately 50% of the cut-off frequency(from the square wave test), as the characteristic is normally flat up to this point.

4013.1.2 Calibration/conversion:
Calibration equipment:

The calibration, whether it is performed with a dedicated calibrator or with a pitotstatic tube as reference, constitutes a major source of uncertainty. The error is stochastic
with a normal distribution and the relative standard uncertainty can be expressed as:
U (U cal ) =1
× STDV (U calibrator (% ))100

The calibrator uncertainty is often given as a relative standard uncertainty, acal , inpercent plus a constant contribution bcal in m/s :STDV (U calibrator ) = ± a(% ) + bcal (m / s )m/s.

The constant contribution bcal may be normally neglected at velocities above 5
acal%

Good dedicated calibrator±1

Pitot-static tube with calibrated micro-manometer (Ucal>2
m/s)

±2%

bcal

m/s

±0.02

Linearisation (Conversion):

The linearisation uncertainty is related to the curve fitting errors. It is stochastic
with a normal distribution and its relative standard uncertainty can be calculated from:
U (U lin ) =1
× STDV (DU lin (% ))100

where STDV(DUlin) is the standard deviation of the curve fitting errors in thecalibration points in %.

13.1.3 Data acquisition related uncertainties
A/D board resolution

The resolution uncertainty is stochastic with a square distribution and its relative
standard uncertainty can be expressed as:
U (U res ) =1 E AD ¶U
× n ×
¶E
3 U 2

1

×

where EAD is the A/D board input range, n is its resolution in bits, U the velocity
and ¶U/¶E is the slope (sensitivity factor) of the inverse calibration curve, U=f(E).

4113.1.4 Uncertainties related to experimental conditions
Probe positioning

The positioning uncertainty relates to the alignment of the probe in theexperimental setup after calibration. The uncertainty is stochastic with a square
distribution and its relative standard uncertainty can be expressed as:
U (U pos ) =1
3

× (1 - cosq )Normally a probe can be positioned with an uncertainty Dq=1°.
Temperature variations

Temperature variations from calibration to experiment or during an experimentintroduce systematic errors. If not corrected, a change in temperature changes the sensor
over-temperature and contributes as a stochastic uncertainty with rectangular
distribution. The relative standard uncertainty is:
1

1
1
æA
ö
U (U temp ) =× ×× ç × U -0.5 + 1÷
3 U Tw - T0 è Bø0.5

where Tw is the sensor temperature, T0 the ambient reference temperature, and DT
is the difference between the ambient reference temperature and the temperature during
the measurement.
This estimate is based on the power law calibration function:(

E 2 = (Tw - T0 ) × A + B × (U cal )0.5) = (T - T ) × (A + B × (r × U ) )
0.5

w

0

1

Since the velocity Ucal actually represents the mass flux, rU, variations in density,r , with temperature will add to the uncertainty, if not accounted for. In gases, this gives
following relative standard uncertainty:
U (U r ,T ) =1
3

× Dr ,T =

DT
3 273

1

×

Ambient pressure variations

Ambient pressure changes also influence the density and hence the calculated
velocity. It contributes as a stochastic uncertainty with rectangular distribution withfollowing relative standard uncertainty:
U (U r , P ) =1 æ P0 ö÷×ç
3 çè P0 + DP ÷ø

Gas composition, humidity

Under normal conditions changes in gas composition are mainly caused bychanges in humidity. The uncertainty is stochastic with a rectangular distribution having
a relative standard contribution of:42

U (Uhum ) =1 ¶U× DPwv
3 U ¶Pwv

1

×

The influence on the heat transfer is very small, ¶U/¶Pwv »0.01·U per 1 kPachange in water vapour pressure Pwv.

13.1.5 Velocity sample uncertainty
The relative expanded uncertainties on a single velocity sample obtained with asingle-sensor hot-wire probe in air, can be summarized in the following table:
Input data are: Tw-T0=200 °C, U=15 m/s, A=1.396, B=0.895, ¶U/¶E=46.5 m/s/volt
Source ofuncertainty

Input
varians

Typicalvalue

Relative output varians

1

× Dy iU

Typicalvalue

1
× Dy iU

Coverage
factork

Relativestandard
uncertainty

Dxi

Dxi

Calibrator

DUcal

1%

2·STDV(100·DUcal)

0.02

2

0.01

Linearisation

DUfit

0.5%

2·STDV(100·DUfit)

0.01

2

0.005

A/D
resolution

EAD

10
volts

1 E AD ¶U
×
×
U 2n
¶E

Ö3

0.0013

Ö3

»0

0.013

Ö3

0.008

0.004

Ö3

0.002

0.01

Ö3

0.006

n

12 bitProbe
positioningq1°

Temperature
variations1)

DT

1 °C

1-cosq

0.000
8
0.000
15

1 1
× × Dyik U

DT1
æ A -0,5 ö×× ç ×U+ 1÷
U Tw - T
B
è
ø
0

(

Temperature
variations2)

DT

Ambient
pressure

DP

1 °C

)

DT

273

10
kPa

P
0
P0 + DP43

Humidity

DPwv

1 kPa

1

×

¶U

U ¶Pwv

× DPwv

0.000
6

Ö3

»0

2

æ1 1
ö
Relative expanded uncertainty : U(Usample) = 2 × å ç × × Dyi ÷ = 0.030 = 3 %
èk U
ø
3)

Table 1. Error sources and uncertainties for a single velocity sample acquired with a
CTA under typical experimental conditions including calibrator uncertainty.
1)

Uncertainty due to change in sensor overtemperature alone.

2)

Uncertainty due to change in air density with temperature alone.

3)

The two uncertainties from temperature variations are inter-correlated and should be added
arithmetically before they are added geometrically to the other uncertainties.

From above example it appears that the voltage from a CTA with a wire probe canbe acquired and converted into a velocity sample with an uncertainty of approximately 1% with a 95% confidence interval with reference to the calibration and neglecting theuncertainty of the calibrator itself. When the uncertainty of calibrator is included, theuncertainty of a velocity sample increases to typically 3%. The major contributions
come from the calibrator, temperature variations in the flow and the linearisation (curve
fitting). Variations in atmospheric pressure may also play a role.

13.2 Uncertainty of reduced data.
The uncertainty of reduced data (mean velocity, standard deviation of velocityetc.) depends on the uncertainty of the individual samples as described in chapter 11.1
and on how true the data represents the flow. As the data presents a random process the
choice of sampling rate and number of samples is most important for the uncertainty
due to the sampling process. The criteria for this choice are shortly described in chapter
7, where it is demonstrated how the number of samples can be calculated on the basis of
known turbulence intensity, and the required uncertainty and confidence level.
For further reading please consult the literature.

14. Advanced topics.
Very low velocities.

At very low velocities the heat transfer from the wire is governed by naturalconvection. This means that the cooling not only depends on the magnitude of thevelocity but also its orientation with respect to the gravity field. The influence of naturalconvection starts around 0.2 m/s for wire probes and takes over completely around 0.030.04 m/s. In this range it is important that the probe has the same orientation withrespect to the velocity field during calibration and measurement [22].

44High velocities, compressible flows.

At high velocities the flow becomes compressible and effects fromcompressibility should be taken into account. In practice this means that pressure andvelocity should be measured simulatneously. The correction is quite complicated and isvery often neglected [33],[48], [55].
Rarified flows (low pressures).

When the pressure decreases the mean free path of the molecules increases. If theKnudsen number Kn (wire diameter divided by free mean path) gets smaller than 100,
the heat transfer becomes a function of both velocity and Knudsen number (or pressure).
For a 5 micrometer diameter wire the Kn is around 100 at atmospheric conditions. Iflower pressures occur, it should be considered to use fibre-film probes instead of wireprobes [8].
Wall effects.

When the wire is placed close to a solid wall, heat will be conducted through theflowing medium to the wall. If not corrected for this will cause the velocity to bemeasured too high. The wall influence starts at y+ £ yUt/n = 3.5 (y= distance to thewall, Ut =friction velocity and n=kinematic viscosity). The critical wall distance istypically 0.1 to 0.2 mm depending on free stream velocity [53], [62], [22].
Very high turbulence, revering flows.

If the turbulence is very high, above 30% or more, or in reversing flows, wherethe velocity vector falls outside the opening angle of the sensor array, the results will beincorrect. Such flows can be measured correctly with flying hot-wire systems, where theprobe is moved through the flow field with a speed high enough to move the resulting
velocity vector inside the opening angle. After linearisation the flying speed is
subtracted from the longitudinal velocity component [52], [56].
Wall shear stress.

Wall shear stress can be measured with flush mounting film probes mounted in
the wall. The heat transfer can then be expressed as a function of the wall shear stress.
The probes have to be calibrated in a known shear. It should be noted that the secondary
heat transferred to the wall changes the frequency response of wall mounted probes ascompared to freely mounted film probes [25], [37].
Two-phase flows.

As the heat transfer is much bigger in liquids than in gases, a hot wire (or hotfilm) will clearly distinguish between liquid and gas phase. This can be utilised tomeasure the passage of for example air bubbles in water [20].

45Binary mixtures.

The heat transfer to gases depends to some extent on the heat conductivity of thegas. The heat transfer from a wire can therefore be used to measure the concentration inbinary mixtures. This is done in practice by placing the wire in a sonic nozzle(aspirating probe), where the probe is exposed to a constant velocity independent of thefree stream velcocity and therefore primarily responds to changes in heat conductivity[44].

15. THE CTA ANEMOMETER , BASIC PRINCIPLES
The hot-wire anemometer was introduced in its original form in the first half of the20th century. A major breakthrough was made in the fifties, where it becamecommercially available in the presently used constant temperature operational mode
(CTA). Since then it has been a fundamental tool for turbulence studies. The
measurement of the instantaneous flow velocity is based upon the heat transfer between
the sensing element, for example a thin electrically heated wire or a metal film, and thesurrounding fluid medium. The rate of heat loss depends on the excess temperature of
the sensing element, its physical properties and geometrical configuration, and theproperties of the moving fluid. A hot-wire anemometer provides reliable information on
the fluctuating flow component in both the space and time domains.

15.1 Characteristics of the hot-wire sensing element,
15.1.1 Static characteristics - stationary heat transfer
The relationship between the fluid velocity and the heat loss of a cylindrical wire isbased on the assumption that the fluid is incompressible and that the flow around thewire is potential. When a current is passed through wire, heat is generated (I2Rw).
During equilibrium, the heat generated is balanced by the heat loss (primarily
convective) to the surroundings. If the velocity changes, then the convective heattransfer coefficient will also change resulting in a wire temperature change that will
eventually reach a new equilibrium with the surroundings.
The experimentally obtained static calibration curve is typically plotted as hot-wirevoltage versus flow velocity. It may be described by a power law relationship given interms of the non-dimensional parameters Reynolds number, Re, Nusselt number, Nu,
and the Prandtl number, Pr. Emperically this type of dependency is valid for0.01<Re<104 [15]. Actually the heat loss is influenced by a number of other factors like:natural convection at very low velocities, compressibility effects at high velocities,
density effects at low pressures. Please refer to the Hot-wire literature concerning thesemore specialised matters.

46

15.1.2 Dynamic characteristics, frequency limit.
The hot-wire response can be derived from the nonstationary heat balance equation.
When exposed to changes in flow velocity the wire will not react instantaneously due to
its thermal inertia. This will dampen the variations in wire resistance Rw (and in wire
voltage) and result in flow fluctuations being measured smaller than they actually are.
The wire response alone is far too slow for most turbulence studies, and compensationin the electronics of the anemometer is therefore necessary. By using the ConstantTemperature Anemometer principle, whereby a feed-back amplifier keeps the sensor
resistance constant independent of variations in U, the frequency limit may be increased
up to 1000 times or more [10], [12].

47Governing equation:
Consider a thin heated wire mounted to supports
and exposed to a velocity U.
dQi
W =Q+
dt
W = power generated by Joule heating
W = I2 Rw , recall Rw = Rw(Tw)Q = heat transferred to surroundings
Qi = CwTw =thermal energy stored in wire
Cw = heat capacity of wire
Tw = wire temperature
Static characteristics –stationary heat transfer:
Heat storage in the wire is zero:

W = Q = I 2 R = hA(Tw - T0 )or replacing h with Nu:

I 2 Rw =A
Nuk f (Tw - T0 )d

h = film coefficient of heat transfer
A = heat transfer aread = wire diameter
kf = heat conductivity of fluid
Nu = dimensionless heat transfer coefficient
In the forced convection regime (0.02<Re<140):
Reynolds number: Re =r ×U × d, r = air density, U= velocity and m = air dynamic viscosity.
m

Nu = A1 + B1 · Ren = A2+ B2 Un

I2Rw2 = E2 = (Tw –T0)(A + BUn) “King’s law” [15]. The voltage is a measure of velocity U.

Dynamic characteristics- frequency limit:
Heat storage term added to the stationary heattransfer equation:dT
I 2 R w = R w - R0 A + BU n + C w w
dt

(

)(

)

or expressing Tw in terms of Rw andtemperature coefficient of resistance a0:) aCR dRdt(

I 2 Rw = (Rw - R0 ) A + BU n +

w

0

w

0

This differential equation has the time constant t:t =Cw
a 0 R0 A1 + B1U n - I 2()

Frequency limit (3 dB amplitude damping):

f cp =

12pt

48

15.2 Mechanical design of hot-wire probes
A hot-wire probe for the measurement of high frequency flow fluctuations consists of avery thin wire mounted on some kind of support. The hot-wire material is chosen so as
to fulfil a number of requirements such as: high temperature coefficient of resistance,high specific resistance, high mechanical strength and ability to operate at hightemperatures. Tungsten is far superior to other metals in this respect and is therefore
used, whenever possible. It can be used at wire temperatures up to 300 ˚C and at
velocities up to the supersonic range. Most hot-wires have a diameter of 5 mm and alength of approximately 1mm. The wire is spot-welded to needle-shaped prongs,
normally made of stainless steel. The prongs are embedded in a probe body, whichelectrically connects to the anemometer via a probe cable.

15.3 Spatial resolution of hot-wires.
The space volume over which the hot-wire output averages depends on the wire size, its
frequency limit and the flow velocity. The resolution length in the direction of the flow
will be directly proportional to the mean velocity and inversely proportional to theupper frequency limit of the hot-wire inclusive of the anemometer circuit. The upper
frequency limit of an anemometer should be chosen so that the resolution length in the
direction of the mean flow velocity is of the same order of magnitude as the length of
the wire. At 50 m/s an anemometer with a frequency limit of 25 kHz a typical wireprobe will have a spatial resolution of 1 mm in the streamwise direction.

15.4 Directional sensitivity of hot-wires.
The heat transfer relation for a hot-wire, which forms basis for its static calibration,
assumes that the veocity vector is directed normal to the wire. In fact the heat transfer
strongly depends on the angle between the velocity vector and the wire. In the case of
an ideal sensor, where there is no heat conduction to the prongs, the heat transfer varies
with the cosine of the angle between the velocity and the wire normal. In reality heat is
conducted to the prongs and a directional sensitivity factor k (yaw-factor), which
descibes the prong interference, has to be introduced. In a 3-dimensional flow, wherethe velocity moves out of the wire-prong plane, the heat transfer will increase due toincreased cooling of the prongs. This can be described by the pitch factor h.
Individual directional calibration of hot-wires, in addition to velocity calibrations,
makes it possible to measure both velocity magnitude and direction in 2 or 3dimensional flows using probes with 2- or 3-wires arranged in orthogonal arrays.

49

Probe design:
Tungsten wire is spot-welded to stainless steel
prongs embedded in a ceramic tube.
Gold-plated probes have plated wire ends inorder to minimise prong effects.

Spatial resolution:
Hot-wire resolution lx in streamwise direction:lx =U mean2 f cp[5].

Umean = mean velocity
fcp = frequency limit
High spatial resolution at high velocity
requires high bandwidth
Directional sensitivity:
Finite wire response includes yaw and pitch
Sensitivity [24], [29].:()
U (q ) = U (0 ) (cos q + h sin q )U (a ) = U (0 ) cos 2 a + k 2 sin 2 a
2

2

2

2

2

2

2

θ=0
a=0

General response in 3-D flows:222
2
U eff = U x + k 2U y + h 2U z
U(0):
Ueff:

actual velocity in the flow
effective cooling velcoity(calculated from velocity calibration)a:
yaw angle (angle between velocity
and wire normal)
θ:
pitch angle (agle between velocity
and wire wire-prong plane)k:yaw factorh:pitch factor(x,y,z): probe oriented coordinate system50

15.5 The Constant Temperature Anemometer.
The constant temperature anemometer is designed with the purpose of eliminating
the influence of the thermal inertia of the wire in fluctuating flows, so that the frequency
limit of the instrument is mainly determined by the electronic circuitry. This isachieved by supplying electrical energy to the wire at exactly the same rate as heat islost to the surrounding fluid medium and at the same time. Since the wire temperature isthus kept constant irrespective of the flow velocity, the importance of the heat
capacitance of the wire is greatly diminished.
The operation of the CTA anemometer can be explained as follows:
The hot-wire is placed in one arm of a Wheatstone bridge opposite a variable
resistor, which defines the operating resistance, and hence the operating temperature of
the hot-wire. In the case the bridge is in balance, no voltage difference exists across its
diagonal. Now, if the flow velocity increases, the wire resistance will tend to decrease
and an error voltage will be present at the input of the current regulating amplifier. This
will cause the probe current to increase. The wire will heat and increase in resistance
until the balance is restored. Because of the high gain of the current regulating
amplifier, a condtion of bridge balance exists, which is practically independent of theflow velocity past the wire. The wire time constant is thus reduced by a factor of several
hundred times from fractions of a milliseconds to some few microseconds. The probe
current is represented by the voltage drop across the bridge. As all resitances in thebridge are constant, the squared output voltage E2 directly represents the heat loss fromthe wire and can replace Q in the heat transfer equation for the wire.

51

CTA anemometer principle diagram:
Main components are:
Wheatstone bridge:
Probe: Rw
Overheat resistor: R3
Top resistors: R1 and R2
Feedback loop:
Amplifier: G
Gain shape control: S*
Filter: F*
Power amplifier: P*
Cable compensation: C** not shown in principle diagram.
Improved wire response:
The servo-loop amplifier increases the wire
frequency limit:

f c ,CTA = 2aSRw f c , wire
tw = wire time constant alonea = overheat ratio
Rw = wire resistanceS = amplifier gain
Typical CTA frequency response:
Typical frequency response (amplitude
damping and phase lag) of CTA with
5 mm wire probe.

Typical velocity response:
The relation between the CTA output E and thevelocity U repesents the probe calibration, fromwhich the transfer function U = f(E) is derived.

æEA(Tw - T0 ) ö÷÷
U = çç
B
è B
ø
2

1
n

or

U =C 0 +C1 E + C 2 E 2 + C 3 E 3 + C 4 E 452

16. REFERENCES
The hot-wire anemometer literature counts more than 1200 titles covering almost
all aspects of anemometry, ranging from the design of advanced electronic circuitry
over sophisticated signal interpretation and data reductions to practical hints on how tomount and operate a hot-wire in a specific application. H.H. Bruun’s book on Hot-Wire
Anemometry from 1995 is the most comprehensive reference text book for the selection
and use of hot-wire/hot-film anemometry techniques published so far. It contains analmost complete list of references up to the date of printing. Other valuable sources are
DISA Information 1965-1985, which was replaced by Dantec Information 1985-1995.
The below short list of references contains some of the more important text books
and papers but does not intend to be neither complete, nor fully representative. It should
be regarded only as a tool, by which one can get either immidiate help or be guided tomore adequate references. Copies of the listed papers are available from Dantec
Dynamics on request.
Text books on Hot-wire Anemometry:
1. Bradshaw, P.: “An introduction to Turbulence and its Measurement”. Pergamon Press 1971
2. Bruun, H.H.: “Hot-Wire Anemometry, Principles and Signal Analysis”. Oxford Science
Publications 1995.
3. Compte-Bellot, G.:”Hot-wire Anemometry.” The Handbook of Fluid Dynamics edited by
R.W. Johnson CRC Press LLC, 1998.
4. Fingerson, L.M.:”Thermal Anemometers.” Fluid Mechanics Measurements. Edited by R.J.
Goldstein. Hemisphere Publishing/Springer 1983.
5. Kovásnay, L.S.G.:” Turbulence Measurements”. Physical Measurements in Gas Dynamics
and Combustion. Edited by R.W.Ladenburg et al. Princeton University Press 1954.
6. Lomas, C.G.: “Fundamentals of Hot Wire Anemometry”. Cambridge University Press 1986
7. Sandborn, V.A.:”Resistance Temperature Transducers”. Metrology Press 1972.

Papers on Hot-wire Anemometry in general:
8. Baldwin, L.V. et al.:”Heat Transfer From Transvers and Yawed Cylinders in Continuum,
Slip, and Free Molecule Air Flows.” Journal of Heat Transfer, May 1960.
9. Bradshaw, P.:”Thermal methods of flow measurement.” J. Phys. E.: Sci. Instrum. 1968
Series 2 Volume 1.
10. Freymuth, P.:”Frequency response and electronic testing for constant-temperature hot-wireanemometers.” Journal of Physics E.: Scientific Instruments 1977 Volume 10, 705-710.
11. Freymuth, P.:”Calculations of square wave test for frequency optimised hot-film
anemometers.” Journal of Physics E.: Scientific Instruments 1981 Volume 14, 238-240.
12. Freymuth, P.:”Interpretations in the control theory of thermal anemometers.” Meas. Sci.
Technol. 8 (1997) 174-177.
13. Freymuth, P.:”Second or third order control theory for constant-temperature hot-wireanemometers.” Experiments in Fluids 23 (1997) 175-170.
14. Jørgensen, F.E.:”The computer-controlled constant-temperature anemometer. Aspects of
set-up, probe calibration, data acquisition and data conversion.” Meas. Sci. Technol. 7(1996) 1378-1387.
15. King, L.V.:”On the convection of heat from small cylinders in a stream of fluid:
Determination of the convectiomn constants of small platinum wires with applications to
hot-wire anemometry.” Phil. Trans. Roy. Soc. A214 (1914), 373-432

53

16. Weiss, J. et al.:”Method for the determination of frequency response and signal to noise
ratio for constant-temperature hot-wire anemometers”. Review of Scientific Instruments,
Volume 72, Number 3, March 2001.

Papers on Probes and probe response:
17. Bellhouse, B.J. et al.:”Low-Frequency Characteristics of Hot-Film Anemometers.” DISA
Information No. 6. 1968.
18. Bergström, H. et al.:”Calibration of a Three-Axial Fiber-Film System for Meteoroligical
Turbulence Measurements.” Dantec Information No. 5, 1987.
19. Bonis, M. et al.:”A Heat Transfer Law for a Conical Hot-film Probe in Water.” DISA
Information No. 14, 1973.
20. Bremhorst, K.. et al.:”Response of hot-wire anemometer probes to a stream of air bubbles ina water flow.” J. Phys. E.: Sci. Instrum. Volume 9, 1976.
21. Chew, Y.T. et al.:”The directional sensitivities of crossed and triple hot-wire probes.” J.
Phys. E.: Sci. Instrum. 21 (1988) 613-620.
22. Christman, P.C. et al.:”Hot-wire anemometer behaviour in low velocity air flow.” J. Phys.
E.: Sci. Instrum. 1976 Volume 14, 1981.
23. Collis, D.C. et al.:”Two-dimensional convection from heated wires at low Reynolds
numbers.” J. Fluid Mech., 6, (1959), 357-384.
24. Friehe, C.A. et al.:”Deviations From the Cosine Law for Yawed Cylindrical Anemometer
Sensors.” Journal of Applied Mechanics, Transactions of the ASME 68-WA/APM-16.
25. Geremia, J.O.:”Experiments on the Calibration of Flush Mounted Film Sensors.” DISA
26. Gieseke, T.J.:”An experimental approach to the calibration and use of triple hot-wireprobes.” Experiments in Fluids 14, 305-315 (1993).
27. Hollash, K. et al.:”Calibration of Constant-Temperature Hot-Wire Anemometers at Low
Velocities in Water with Variable Fluid Temperature.” Journal of Heat Transfer, ASME
Paper No. 71-HT-9.
28. Johnson, F.D. et al.:”A variable angle method of calibration for X-probes applied to wallbounded shear flow.” Experiments in Fluids 2, 121-130 (1984).
29. Jørgensen, F.E.:”Directional Sensitivity of Wire and Fibre-Film Probes.” DISA Information
No. 11. 1971.
30. Kassab. S.Z.:”Effect of the hot-wire length on the determination of the length scale of large
eddies.” Meas. Sci. Technol. 2 (1991) 647-652.
31. Ligrani, P.M. et al.:”Subminiature hot-wire sensors: development and use.” J. Phys. E.: Sci.
Instrum. 20 (1987).
32. Marasli, B.:”A calibration technique for multiple-sensor hot-wire probes and its application
to vorticity measurements in the wake of a cylinder.” Experiments in Fluids 15, 209-218(1993).
33. Norman, B. :”Hot-wire Anemometer Calibration at High Subsonic Speeds.” DISA
Information No. 5. 1967.
34. Perry, A.E. et al.:”Vibration of hot-wire anemometer filaments.” J. Fluid Mech. (1967), vol.
50, part 4, pp. 815-825.
35. Schewe, J. et al.:”Error-tolerant calibration of dual sensor probes used in turbulent wallboundary layer.” Experiments in Fluids 9, 285-289 (1990).
36. Strohl, A. et al.:”Aerodynamic Effects Due to Configuration of X-Wire Anemometers.”
Journal of Applied Mechanics, Transactions of the ASME 73-APM-P.
37. Sumer, B.M. et al.:”Two-component hot-film probe for measurement of wall shear stress.”
Experiments in Fluids 15, 380-384 (1993).
38. Tagawa, M. et al.:”Evaluation of X-probe response to wire separation for wall turbulencemeasurements.” Experiments in Fluids 12, 413-421 (1992).
39. Teo, C.J. et al.:”The dynamic response of a hot-wire anemometer: IV. Sine wave voltage
pertubation testing for near-wall hot-wire/film probes and the presence of low-frequency
response characterisics.” Meas. Sci. Technol. 12 (2001) 37-51.
54

40. Turan, Ö.F. et al.:”Effect of structural vibrations on hot-wire probe response.” Widell,
K.E.:”Stresses and Deformations in Hot-Wire Probes.” DISA Informatioon No. 2, 1965
41. Yeung, C.P. et al.:”Numerical calibration and verification tests of othogonal triple-hot-wireprobe.” Meas. Sci. Technol. 4 (1993) 1446-1456.
42. Zank, I.:”Sources of Errors and Running Calibration of Three-Dimensional Hot-Film
Anemometers Especially near the Sea Surface.” DISA Information No. 26. 1981.

Papers on methods and applications:43. Abdel-Rahmann, A.A.:”An X-array hot-wire technique for heated turbulent flows of low
velocity.” J. Phys. E.: Sci. Instrum. 22 (1989) 638-644.
44. Brown, G.L. et al.:”A Small, Fast-Response Probe to Measure Gas Composition of Binary
Gas Mixtures.” AIAA Journal, Vol. 10, No. 5, 1972, 649-652.
45. Bruun, H.H.et al:”Velocity component measurements by X hot-wire anemometry.” Meas.
Sci. Technol. 1 (1990) 1314-1321.
46. Butterfield, R.G.:”Application of thermal anemometry and high-frequency measurement ofmass flux to aeolian sediment transport.” Geomorphology 29 (1999) 31-58.
47. Chew, Y.T. et al.:”A critical evaluation of the explicit data analysis algorithm for a crossed
wire anemometer in highly isotropic flow.” Meas. Sci. Technol. 1 (1990) 775-781.
48. Demin, V.S.:”Interpretation of Hot-Wire Anemometer Readings in a Flow with Velocity,
Pressure and Temperature Fluctuations.” Fluid Mechanics- Soviet Research, Vol. 2, No. 3,
May-June 1973.
49. Frota, M.N.:”Analysis of the Uncertainties in velocity Measurements and Technique for
Turbulence Measurements in Complex Heated Flows with Multiple Hot Wires”. Stanford
University 1982.
50. Gaullier, C.:”Measurement of Air Velocity by Means of a Triple Hot-Wire Probe.” DISA
Information No. 21. 1977.
51. Hoffmeister, M.:”Using a Single Hot-Wire Probe in Three-Dimensional Turbulent Flow
Fields.” DISA Information No. 13. 1972.
52. Kelso, R.M. et al.:”A novel flying hot-wire system.” Experiments in Fluids 16, 181-18684(1994).
53. Khoo, B.C. et al.:”On near-wall hot-wire measurements.” Experiments in Fluids 29, 448460 (2000).
54. Löfdahl, L.:”Hot-Wire Techniques for the Determination of the Reynolds Stress Tensor inThree-Dimensional Flows”. Dantec Information No. 35, 1986.
55. Smiths, A.J. et al.:”Constant Temperature Hot-Wire Anemometer Practice in SupersonicFlows, Part 1: The Normal Wire:” Experiments in Fluids 1, 83-92 (1983).
56. Thompson, B.E.:”Appraisal of a Flying Hot-wire Anemometer”. Dantec Information No. 4,
1987.
57. Van Dijk, A.:”Aliasing in one-point turbulence measurements.” Dissertation, Technical
University Delft 1999.
58. Wark, C.E. et al.:”A rotating hot-wire technique for spatial sampling of disturbed andmanipulated duct flows.” Experiments in Fluids 9, 191-196 (1990).
59. Wyngaard, J.C.:”Measurement of small-scale turbulence structure with hot-wires.” J. Phys.
E.: Sci. Instrum. Series 2 Volume 1, 1968.

Papers on disturbing effects:
60. Bearman, P.W.:”Corrections for the Effect of Ambient temperature Drift on Hot-Wire
Measurements in Incompressible Flows.” DISA Information No. 11. 1971.
61. Durst, F. et al.:”Influence of humidity on hot-wire instruments”. Meas. Sci. Technol. 7(1996) 1517-1528.
62. Hebbar, K.S.:”Wall Proximity Corrections for Hot-Wire Readings in Turbulent Flows.”
DISA Information No. 25. 1980.

55

63. Löfdahl, L. et al.:”The influence of temperature on the measurements of Reynolds stresses
in shear free turbulence near a wall.” Experiments in Fluids 25, 160-164 (1998).
64. Martinez- Val, R. et al.:”Sensor contamination Effects in Hot-Wire Anemometry in Air.”DISA Information No. 27. 1982.
65. Mojola, O.O.:”The Effects of Orientation of a Hot-Wire Probe Body in Turbulent Shear
Flow.” DISA Information No. 23. 1978.
66. Firasat Ali, S.:”Hot-wire anemometry in moderately heated flow.” Rev. Sci. Instrum., Vol.
46, No. 2, 1975.
67. Bremhorst, K.:”Effect of fluid temperature on hot-wire anemometers and an improved
method of temperature compensation and linearisation without use of small signal
sensitivities.” J. Phys. E.: Sci. Instrum. Vol. 18, 1985.
68. Schubauer, G.B.:”Effect of humidity in hot-wire anemometry.” National Bureau ofStandards, Research Paper RP850, 1935.

56