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Experimental Aerodynamics
Lecture 2: Wind Tunnel Instrumentation
G. Dimitriadis and T. Andrianne
Experimental Aerodynamics Experimental Aerodynamics
Experimental Aerodynamics
Introduction
•! The ability to simulate a real flow in a wind tunnel is not useful in itself
•! The simulated flow must be observed for the experiment to have some use
•! The simplest type of observation is by just looking at the experiment
•! More precise observations can be obtained using several types of instrumentation
Experimental Aerodynamics
Scope of the lecture
•! Airspeed measurement –!Pitot tube –!Hot wire anemometry
•! Flow visualization –!Qualitative (wool, clay, oil, smoke, !) –!Quantitative (PIV, PSP, LDA,!)
•! Force measurement
Experimental Aerodynamics
Scope of the lecture
•! Airspeed measurement –!Pitot tube –!Hot wire anemometry
•! Flow visualization –!Qualitative (wool, clay, oil, smoke, !) –!Quantitative (PIV, PSP, LDA,!)
•! Force measurement
Experimental Aerodynamics
Working section airspeed •! The most basic parameter in the wind
tunnel working section is the airspeed •! The airspeed can be measured using a
Pitot-static tube (developed in the 18th century by Henri Pitot)
•! The Pitot-static tube measures the total and static pressure in the wind tunnel working section
•! The difference between these two pressures is the dynamic pressure
Experimental Aerodynamics
Pitot-static Tube D
8 holes equally spaced on the periphery
8D 16D
3D
Total head connection
Static connection, p
Air velocity, V
pt = p +12!V 2
V =2 pt ! p( )
"
Experimental Aerodynamics
Pitot-static tube accuracy •! Pitot-static tubes can be accurate to 0.1%. •! Some corrections must be made for
Reynolds number and proximity to a wall. •! The total head measurement is accurate
as long as the angle between the tube and the flow is less than 3o.
•! The leading edge of the pitot affects the static pressure downstream. The static pressure holes must be placed sufficiently downstream to avoid this effect.
Experimental Aerodynamics
Speed setting •! In some cases it is not practical to use a pitot-static
tube in the working section. •! The model may interfere with the pitot
measurement or vice versa •! In such cases the pitot-static tube can be placed in
the settling chamber (ahead of the contraction cone) or just ahead of the working section.
•! The pitot-static tube placed in these positions can be calibrated to yield the correct working section airspeed using calibration runs (no model) and a second pitot-static tube in the working section.
Experimental Aerodynamics
Working section static temperature
•! The calculation of the test section airspeed from pitot-static tube data requires knowledge of the air density
•! The density can be obtained from the state equation if the static pressure and temperature are known.
•! The temperature can be measured using a wall-mounted thermometer or other temperature probe (static temperature is constant in a boundary layer)
V =2 pt ! p( )
"
Experimental Aerodynamics
Other uses of Pitot tubes
•! Static pressure measurement –!Long static tube
•! Flow direction measurement –!5-hole probe
•! Boundary layer measurement –!Total head rake
Hot wire
5-hole probe
Total head rake
Experimental Aerodynamics
Other uses of Pitot tubes
And of course ! Aircraft airspeed
Hot wire
5-hole probe
Total head rake Supersonic > corrections needed !
Experimental Aerodynamics
Scope of the lecture
•! Airspeed measurement –! Pitot tube –!Hot wire anemometry
•! Flow visualization –!Qualitative (wool, clay, oil, smoke, !) –!Quantitative (PIV, PSP, LDA,!)
•! Force measurement
Experimental Aerodynamics
•! Blowing on hot food decreases its temperature
•! Same principle for HW •! Tungsten wire •! Different types:
–! CCA (current) –! CVA (voltage) –! CTA (temperature)
Hot wire anemometry
5-hole probe
Total head rake
Experimental Aerodynamics
Convective heat exchange Q = (Tw-T0) Aw h = A + B Un (n ~ 0.5)
where Tw = HW temperature T0 = Fluid temperature Aw = HW surface h = heat transfer coefficient (depends on fluid and wire characteristics
Hot wire anemometry
5-hole probe
Total head rake
Experimental Aerodynamics
CTA principle •!Servo amplifier keeps the bridge in balance (by controlling the current) •!Temperature is kept constant •!Bridge voltage (E) represents the heat transfer = direct measure of the fluid velocity
Hot wire anemometry
Total head rake
Thermal inertia of HW << High gain of the servo amplifier > Very fast response
Experimental Aerodynamics
Hot wire anemometry
5-hole probe
Total head rake
Source: Dantec Dynamics Posters
+ High frequency response > Study of boundary layers, turbulence of a flow field
- Intrusive, accurate but small spatial resolution
Experimental Aerodynamics
Hot wire anemometry Calibration
5-hole probe
Total head rake
Experimental Aerodynamics
Hot wire anemometry Calibration
5-hole probe
Total head rake Calibrated Airspeed (m/s)
Volta
ge (V
)
U = C0 + C1E + C2E2 + C3E3 + C4E4 + C5E5
ECORR = ETw !T0Tw !Tmeas
"
#$
%
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0,5
Experimental Aerodynamics
Hot wire anemometry Different types of probes
5-hole probe
Total head rake
1 mm long and 5 "m in diameter
1D 2D 3D
Experimental Aerodynamics
Scope of the lecture
•! Airspeed measurement –!Pitot tube –!Hot wire anemometry
•! Flow visualization –!Qualitative (wool, clay, oil, smoke, !) –!Quantitative (PIV, PSP, LDA,!)
•! Force measurement
Experimental Aerodynamics
•! It is often interesting to observe the simulated flow around the model in the wind tunnel.
•! Unfortunately air is colorless and transparent •! Several different methods exist:
Flow visualization
Qualitative methods Wool (cotton) tufts China clay Oil film Smoke
Quantitative methods Particle Image Velocimetry (PIV and Tr-PIV) Pressure Sensitive Paint (PSP), Laser Doppler Anemometry (LDA)!
Experimental Aerodynamics
Scope of the lecture
•! Airspeed measurement –!Pitot tube –!Hot wire anemometry
•! Flow visualization –!Qualitative (wool, clay, oil, smoke, !) –!Quantitative (PIV, PSP, LDA,!)
•! Force measurement
Experimental Aerodynamics
Oil flow visualization •! Lubricating oil is applied in small
dabs on several locations on the model.
•! When the wind is turned on, the oil will follow the local streamlines.
•! Oil flows will indicate the boundary of flow separation, since the oil cannot cross the separation boundary.
•! Thinning down the oil can also indicate the laminar-turbulent flow transition boundary.
•! Often, color pigments are added to the oil in order to aid visualization. Sometimes the paint is fluorescent and can be lit by a UV light.
Experimental Aerodynamics
Smoke Flow Visualization
•! Producing smoke is not easy. Burning stuff is not recommended.
•! The most popular smoke production methods are: –!Fog generators, such as those used in
night clubs. These are good for thick smoke streaks
–!Smoke wire
Experimental Aerodynamics
Smoke Wire
Source: Sharul Sham Dol et al. at 4th WSEAS International Conference on Fluid Mechanics and Aerodynamics
Smoke wires only work in low speed and low turbulence conditions! Airspeed < 10m/s
Experimental Aerodynamics
Smoke Wire
Source: Sharul Sham Dol et al. at 4th WSEAS International Conference on Fluid Mechanics and Aerodynamics
Experimental Aerodynamics
Smoke flow visualization examples
Stalled wing
Car
Circular cylinder
Experimental Aerodynamics
Smoke visualization videos •! Flow around Delta wing and ducted fan at low speed •! Flow unsteadiness due to:
–! High angle of attack –! Wind tunnel turbulence –! Smoke generator quality
Experimental Aerodynamics
Scope of the lecture
•! Airspeed measurement –!Pitot tube –!Hot wire anemometry
•! Flow visualization –!Qualitative (wool, clay, oil, smoke, !) –!Quantitative (PIV, PSP, LDA,!)
•! Force measurement
Experimental Aerodynamics
Particle Image Velocimetry •! PIV works on the principle of lighting up small
particles in the airflow using a laser light. •! A laser surface is created in the working
section and a camera is focused on this surface.
•! Particles are injected in the flow. These are light, small and invisible. They can be tiny was droplets
•! When the particles pass under the laser they are lit up and can be photographed by the camera
•! PIV can be also performed in 3D (Stereo PIV)
Experimental Aerodynamics
PIV principle
2D PIV 3D (Stereo) PIV
Experimental Aerodynamics
!"#!"$%&#
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!(#!($%&#
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*++,+,#-./012#
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Tr-PIV principle
Experimental Aerodynamics 77#
Image 1
Image 2
Sub-Image 1
Sub-Image 2
Cross-Correlation Area of search
Tr-PIV – image analysis
Experimental Aerodynamics
PIV Examples
Guerney flap Circular Cylinder
Helicopter rotor
Experimental Aerodynamics
ULg Tr-PIV example Rectangular cylinder undergoing pitch flutter oscillations
Tr-PIV (slow motion)
Experimental Aerodynamics
Advantages and disadvantages •! Tufts:
–! Advantages: easy to install, cheap –! Disadvantages: can affect other measurements, need to choose the right length/rigidity
of fabric, may need strong light and high speed camera, discrete surface-only flow visualization
•! Smoke: –! Advantages: flow visualization of entire sections of the flowfield, beautiful pictures and
movies –! Disadvantages: More suitable for low Reynolds number flows, turbulence mixes the
smoke, can be corrosive and pollutant. •! Clay/Oil:
–! Advantages: easy to apply, cheap, can take pictures after wind has been turned off. –! Disadvantages: surface-only flow visualization, need a lot of experience to mix and apply
correctly, oil requires cleaning. •! PIV:
–! Advantages: flow visualization of entire sections of the flowfield, high speed, can extract quantitative data
–! Disadvantages: expensive instrumentation, many parameters to set, requires a lot of experience, visualization window is small at high frame rates.
Experimental Aerodynamics
Scope of the lecture
•! Airspeed measurement –!Pitot tube –!Hot wire anemometry
•! Flow visualization –!Qualitative (wool, clay, oil, smoke, !) –!Quantitative (PIV, PSP, LDA,!)
•! Force measurement
Experimental Aerodynamics
Aerodynamic load measurements
•! One of the most important functions of wind tunnels is to provide estimates of the aerodynamic loads acting on bodies moving through air.
•! The first such measurement were obtained using actual balances.
•! Since then, aerodynamic load measurement devices are called aerodynamic balances.
Experimental Aerodynamics
Wind tunnel balances
•! There are several types of wind tunnel balance: –! Internal balances: They are placed inside the
model. –!External balances: They are placed around or
under the working section. –!Strain gauge balances: Most modern balances
feature strain gauges –!Rotary balances: for propellers and other
rotating models
Experimental Aerodynamics
Internal balance
•! They usually come in the form of stingers •! They can measure six loads (three forces
and three moments) •! They must be attached near the model s
centre of gravity
Experimental Aerodynamics
External balance
•! External balances come in several degrees of complexity and size.
•! The complexity depends on the number of loads that the balance must measure (maximum of 6).
•! The most advanced type of external balance currently in use is the pyramidal balance.
Experimental Aerodynamics
External balance design
Experimental Aerodynamics
VKI, 6-comp balance for L-2A
Experimental Aerodynamics
1-component balance
•! The ULg wind tunnel has a very simple 1-component balance mounted under the turntable.
•! It measures lift only using a load cell.
•! Drag and side force can be measured using a strain gauged support on which the model can be attached
Experimental Aerodynamics
Horizontal axis balance
•! The ULg wind tunnel also features a horizontal axis balance.
•! The balance features four vertical force sensors, two horizontal force sensors and a moment sensor.
•! It can measure all 6 aerodynamic loads but the model must be mounted on the horizontal axis.
Experimental Aerodynamics
ULg horizontal axis balance
Force sensor
Torque sensor
Horizontal axis balance
Experimental Aerodynamics
Rotating balances •! For helicopter rotors, propellers, wind
turbine rotors etc