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Aerodynamics

Subsonic Wind Tunnels 7Subsonic Wind Tunnel Instruments and 14Accessories

Special Purpose Wind Tunnels 23Supersonic Nozzle 26Supersonic Wind Tunnels 27

Subsonic Wind Tunnels 7Subsonic Wind Tunnel Instruments and 14Accessories

Special Purpose Wind Tunnels 23Supersonic Nozzle 26Supersonic Wind Tunnels 27

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Aerodynamics

Designed for education and training

TecQuipment specially designed the Aerodynamics range of products for teaching. Weplaced emphasis on ease of use, reliability and safety. Whether used by lecturers todemonstrate basic principles or advanced ideas, or by students for project work, theequipment gives valuable hands-on experience. This experience is not always possible orpractical with large-scale industrial or complex research facilities.

First principles

At introductory level, the range includes our Modular Air Flow Bench. This is a standardunit with eight interchangeable experiments, each one designed specifically to teach animportant first principle, such as Bernoulli’s equation or boundary layer. This equipmentalso comes complete with a dedicated textbook: A First Course in Air Flow. This high-qualityproduct is modular to make it adaptable, versatile and cost-effective.

Wind tunnels

The quality and features of our wind tunnels make them ideal for education, for exampleour comprehensive Subsonic Wind Tunnel. This is a compact, realistic and high-qualitywind tunnel with a wide range of standard instrumentation and models. To maximiseflexibility, the engineers at TecQuipment can put together packages of models andinstrumentation to meet all your budgetary and laboratory needs. The wind tunnel can alsobe used for student project work and research.

Included in the range are two supersonic wind tunnels, which have full visualisation equipmentand instrumentation. One tunnel has cost-effective, intermittent operation, the other operatescontinuously. The Nozzle Flow Apparatus introduces students to supersonic flow.

Enhancing learning – putting theory into practice

Other equipment in the range includes the unique and very tactile Flight DemonstrationWind Tunnel. This allows students to ‘fly’ an aircraft manually using a control column andthrottle, arranged typically as found in a light aircraft.

In addition, our Flow Visualisation Wind Tunnel allows students to ‘see’ the flow of air,bringing textbook diagrams to life.

Our Fluid Mechanics range (Section 4) includes TecQuipment’s Modular Fluid Power units.These allow demonstrations and studies of the performance of different types of ‘realworld’ air machines (fans and compressors).

Automatic data acquisition

The subsonic and supersonic wind tunnels work with TecQuipment’s new and uniqueVersatile Data Acquisition System (VDAS®). VDAS® allows our equipment to connect to acomputer to provide accurate real-time data capture. Raw data can be transformedinstantly into sophisticated graphs and tables using the VDAS® software and easilyexported to other programs. There are other solutions on the market, but none which offerthe same convenience, functionality or wide range of features.

Look out for the VDAS® logo on our product literature:

For more information visit our website at www.tecquipment.com.

Subsonic Wind Tunnels

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Modular Air Flow Bench andAccessories (AF10–AF18)

Modular Air Flow Bench (AF10)

A fan delivers atmospheric air through a flow-control valve toa plenum chamber. Some of the optional experimentmodules fit to the opening in the plenum chamber.Alternatively, supplied as standard (and fitted), there is anaerodynamically shaped contraction that provides a smalleropening for other experiments. Strong but easy-to-usetoggle fasteners hold the experiment modules to the plenumor the contraction, so that users need no extra tools to fitmost experiments.

Discharge from the experiments is normally downwards. Theair passes down through an outlet in the benchtop andexhausts at the back of the bench. For experiments withsmoke, users can fit flexible ducting to the exhaust to directwaste smoke safely away.

Recommended Ancillaries

• Multi-tube Manometer (AF10a) – Measures severalpressures at the same time. Useful for most experimentmodules.

A mobile bench with a wide range ofoptional modules for experiments in air flow

• Air flow bench with variable air flow controland wide range of optional experimentmodules available for a complete course inair flow

• High levels of safety, ideal for studentexperiments, lecture theatre demonstrationsand project work

• Versatile, easy-to-fit and change experimentmodules

• Includes a textbook – A First Course in AirFlow – by Professor E Markland

• Compact and mobile, with a worktop andshelves

• No installation – only single-phase electricalsupply needed (and simple exhaust for wastesmoke for the AF17)

Experiments

When used with the optional experiment modules (seefollowing pages):

• Demonstration of Bernoulli’s equation (AF11)

• Determination of drag force (AF12)

• Demonstration of a turbulent jet (of air) (AF13)

• Demonstration of boundary layer (AF14)

• Flow around a bend (AF15)

• Jet attachment (AF16)

• Flow visualisation (smoke) (AF17)

• Pressure distribution around a symmetrical aerofoil (AF18)

Alternative Products Page

• Subsonic Wind Tunnel (AF100) 12

• Flight Demonstration Wind Tunnel (AF41) 23

• Flow Visualisation Wind Tunnel (AF80) 25

Modular Air Flow Bench (AF10) andMulti-tube Manometer (AF10a)

Professor E Markland devised this equipment for an introductory course in air flow. Professor Markland is the former Head ofMechanical Engineering at the University of Cardiff. Supplied with the equipment is the textbook, written by ProfessorMarkland. It includes theory, experiments and typical results.

The main (essential) part of the equipment is the Modular Air Flow Bench (AF10). This is a small-scale wind tunnel with anelectric fan and adjustable air flow control. You need this first. You then choose and buy the additional experiment modules(AF11 to AF18) that you need, fitting them to the Air Flow Bench to do the experiments.


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Bernoulli’s Equation Apparatus (AF11)

A transparent duct thatfits on the contraction. Ithas removable linerswhich give a simpleconvergent-divergentpassage. Students canmove a Pitot-static tubealong the axis of theduct to show constanttotal pressure and therise and fall of staticpressure. The significantpressure changes give aconvincingdemonstration ofBernoulli’s equation. Thegeometry allowsstudents to comparecalculations againstmeasurement.

Experiments

• Confirmation of Bernoulli’s equation

• How to use a Pitot-static tube

Drag Force Apparatus (AF12)

Fits on the contraction and shows and compares drag forceon a cylinder, flat plate and aerofoil, each of the sameprojected frontal area. The cylinder has a radial pressuretapping. Students may rotate it within the transparentworking section.

Experiments

• Determination of drag force by measurement of thepressure distribution around the cylinder.

• Determination of drag force by wake traverse, using aPitot tube to infer the velocity distribution andmomentum flux in the wake.

• Comparison of the drag force from pressure distributionand wake traverse with that from the drag balance.

• Comparison of the results for the cylinder with those forthe flat plate and aerofoil, using the drag balance. Round Turbulent Jet Apparatus (AF13)

A cylindrical tubewith anaerodynamicallyrounded entrance.It fits to the plenumchamber. The totalpressure in theemerging jet maybe measured bymeans of a Pitottube mounted in atraverse gear, whichis arranged so thata diametricaltraverse may bemade at varioussections along thejet axis. Severaldiameters may betraversed to checkthe symmetry ofthe jet.

Experiments

• Decay of centre-line velocity

• Velocity profile at various distances along the jet and thedevelopment and spread of the jet.

• Analysis of the velocity profiles, to show how the massflux in the jet increases, the kinetic energy flux decreasesand the momentum flux remains constant along thelength.

Boundary LayerApparatus (AF14)

A flat plate is in atransparent workingsection so that aboundary layer formsalong it. A sensitive,wedge-shaped Pitot tubemounted in a micrometertraverse allows studentsto measure velocity in theboundary layer. Bothlaminar and turbulentlayers may be formed.

Experiments

Measurement of the velocity profile:

• in laminar and turbulent boundary layers;

• in the boundary layer on rough and smooth plates;

• in the boundary layer at various distances from theleading edge of the plate; and

• in the boundary layer on plates subject to an increasingor decreasing pressure gradient in the direction of flow(using the removable duct liners supplied).


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Flow Around aBend (AF15)

A bend fits to thecontraction.Pressure tappingsare at importantplaces along thewall of the bend.

Students connectthe tappings to asuitablemanometer (forexample theoptional AF10a)and take readings.

Experiments

• Pressure distribution along the curved inner and outerwalls.

• Radial pressure distribution and comparison with thatpredicted assuming free vortex velocity distribution.

Jet Attachment Apparatus (AF16)

The technology offluidics hasevolved from avariety of devicesthat exploitphenomena offluid mechanicssuch as transitionfrom laminar toturbulent flowand jetattachment to asolid wall.

In this experiment, a jet emerging from a slit flows against awall to which it attaches. The wall may be swung to deflectthe jet through a large angle without jet attachment. Asecond wall may be introduced at the other side of the jet,which may be switched from one side to the other, as isdone in the fluidic switch of the type called a flip-flop.

Experiments

• Demonstration of the Coanda effect

• Demonstration of the fluidic ‘flip-flop’

Flow Visualisation Apparatus (AF17)

Tapped Aerofoil Module (AF18)

A working section fits to the bench to give flow visualisationfacilities. Non-toxic smoke, produced in a generator(supplied), passes into a rake of tubes that produce smokefilaments which flow through the working section. Theyshow the pattern of flow around obstacles or throughrestrictions. This apparatus makes lots of smoke, so you mustvent the exhaust to the open air. We provide a flexible ductfor this purpose.

Note: The smoke generator uses compressed carbondioxide. Its gas bottle is shipped empty for transportregulations. You must fill the bottle before use.

Experiments

With the models supplied:

• Flow around a cylinder, around an aerofoil and through asharp-edged slit (orifice).

Investigates the pressure distribution around an aerofoil. Itincludes a NACA0020 symmetrical aerofoil mounted in aduct with transparent sides. The duct fits onto thecontraction of the Air Flow Bench.

The aerofoil has pressure tappings on its upper and lowersurfaces, six on each surface. These tappings connect to anintegral manifold, for connection to a suitable manometer(not included). Students find the pressure distributionaround the aerofoil and calculate the lift force. The angle ofincidence of the aerofoil is adjustable and shown by aprotractor scale.

Experiments

• Pressure distribution around an aerofoil

• Lift characteristics and stall angle of an aerofoil

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PILOT SKILLS AND TRANSIENT MOTION

Flight Demonstration Wind Tunnel (AF41) Page 23

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PRINCIPLES OF GUIDANCE SYSTEMS

Gyroscope (TM1004) Page 219

TEMS

SENSORS, STABILITY AND CONTROL

Ball and Beam (CE106) Page 38 Sensor and Instrumentation System (SIS) Page 59Helicopter Model (CE150) Page 45

ENGINE PERFORMANCE

Turbojet Trainer (GT100) Page 258

Equipment for teaching the principles of aerospace engineering

MATERIAL TESTING AND SELECTION

Torsion Testing Machine (SM1001) Page 158 Universal Testing Machine (SM1000) Page 161Rotating Fatigue Machine (SM1090) Page 159

Torsion Testing Machine (SMUniversal Testing Machine (SRotating Fatigue Machine (S

ENGINE AERODYNAMICS

Nozzle Flow Apparatus (AF27) Page 26 Supersonic Wind Tunnels (AF300/AF302) Page 27/30

(30

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1STRUCTURAL STRESSES

Thin Cylinder (SM1007) Page 151 Diaphragm (SM1008) Page 153Strain Gauge Trainer (SM1009) Page 155e 155

ENGINE DYNAMICS

Whirling of Shafts (TM1001) Page 214 Static and Dynamic Balancing (TM1002) Page 218

FUEL TANK LEVEL CONTROL

Level Process Training System (TE3300/04) Page 54 Coupled Tanks Apparatus (CE105) Page 37

CONTROL SURFACE ACTUATION AND CONTROL

Servo Controller (CE110) Page 42 Serv Pag

AERODYNAMICS

Modular Air Flow Bench (AF10–18) Page 7 Subsonic Wind Tunnel (AF100) Page 12

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AUXILARY POWER UNIT

Two-Shaft Gas Turbine (GT185) Page 260 260

STRUCTURE

Various Structures modules (STR2–20) Page 179–201

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Subsonic Wind Tunnel (AF100)

• Saves time and money compared to full-scale wind tunnels or airborne laboratories

• Operates at meaningful Reynolds numbers

• Compact, open-circuit suction design

• Wide variety of experiments in aerodynamics

• Comprehensive selection of optionalinstrumentation, models and ancillaries

• High levels of safety

• Controls and instrumentation convenientlymount on a separate, free-standing frame

• Works with TecQuipment’s Versatile DataAcquisition System (VDAS®) to allowaccurate real-time data capture, monitoringand display on a computer

A compact, practical open-circuit suction wind tunnel forstudying aerodynamics. The wind tunnel saves time andmoney compared with full-scale wind tunnels or airbornelaboratories, and it offers a wide variety of experiments.

The wind tunnel gives accurate results and is suitable forundergraduate study and research projects. TecQuipmentoffers a comprehensive range of optional models andinstrumentation, including a computer-based dataacquisition system.

Air enters the tunnel through an aerodynamically designedeffuser (cone) that accelerates the air linearly. It then entersthe working section and passes through a grill before

Open-circuit subsonic wind tunnel for a widerange of investigations into aerodynamics

Screenshot of the optional

VDAS® software

moving through a diffuser and then to a variable-speed axialfan. The grill protects the fan from damage by loose objects.The air leaves the fan, passes through a silencer unit andthen back out to atmosphere.

A separate control and instrumentation unit controls thespeed of the axial fan (and the air velocity in the workingsection). The control and instrumentation unit also includesmanometers and electrical outlets to supply electrical powerto other optional instruments.

The working section of the tunnel is a square section with aclear roof, sides and floor. The sides are removable. The floorand each side panel has a special position to support theoptional wind tunnel models. Supplied with the wind tunnelare a protractor and a model holder to support andaccurately adjust the angle of any models fitted.

A Pitot-static tube and a traversing Pitot tube fit on theworking section, upstream and downstream of any models.They connect to the manometers of the instrumentation unit(or other optional instruments) to show pressure.

A metal frame supports the wind tunnel. The frame includeslockable castors for convenient mobility.

Electronic sensors on the optional wind tunnelinstrumentation can connect to TecQuipment’s VersatileData Acquisition System (VDAS®, not included). VDAS®allows accurate real-time data capture, monitoring, display,calculation and charting of all relevant parameters on asuitable computer (computer not included).

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Experiments

A wide variety of subsonic aerodynamics experiments (someneed ancillaries), including:

• Flow past bluff and streamlined bodies with pressure andvelocity observations in the wake

• Investigations into boundary layer development

• Influence of aspect ratio on aerofoil performance

• Performance of an aerofoil with flap, influence of flapangle on lift, drag and stall

• Pressure distribution around a cylinder under sub andsuper-critical flow conditions

• Study of characteristics of models involving basicmeasurement of lift and drag forces

• Study of the characteristics of three-dimensional aerofoilsinvolving measurement of lift, drag and pitching moment

• Study of the pressure distribution around an aerofoilmodel to derive the lift and comparison with directmeasurements of lift

• Drag force on a bluff body normal to an air flow

• Flow visualisation


• Modular Air Flow Bench (AF10) 7



• Supersonic Wind Tunnel – Intermittent (AF300) 27

• Supersonic Wind Tunnel – Continuous (AF302) 30

Models Minimum Instrumentation for data acquisition

• Cylinder Model with Pressure Tapping (AF101)• 150 mm Chord NACA0012 Aerofoils (AF104)• 100 mm Diameter Flat Plate (AF105)

• Differential Pressure Transducer (AFA5) x 2• Pitot-Static Traverse (300 mm) (AFA7) and either• Basic Lift and Drag Balance (AFA2) or• Three-Component Balance (AFA3) with Angle Feedback

Unit (AFA4)

• 150 mm Chord NAC0012 Aerofoil with Tappings (AF102) • Differential Pressure Transducer (AFA5) x 2• Pitot-Static Traverse (300 mm) (AFA7)• 32-Way Pressure Display Unit (AFA6)

• 150 mm Chord NACA2412 Aerofoil with Variable Flap (AF103)• Aircraft Model – Low Wing (AF107)• Aircraft Model – High Wing (AF108)

• Pitot-Static Traverse (300 mm) (AFA7)• Differential Pressure Transducer (AFA5)• Three-Component Balance (AFA3) with Angle Feedback

Unit (AFA4)

• Flat Plate Boundary Layer Model (AF106) • Differential Pressure Transducer (AFA5)• 32-Way Pressure Display Unit (AFA6)

This table lists the instruments you need which work with VDAS® for data acquisition.Note: You also need the VDAS® software and frame-mounting VDAS-F interface unit (see page 290).

Models Minimum Instrumentation

• Cylinder Model with Pressure Tapping (AF101)• 150 mm Chord NACA0012 Aerofoils (AF104)• 100 mm Diameter Flat Plate (AF105)

• Basic Lift and Drag Balance (AFA2) or• Three-Component Balance (AFA3)

• 150 mm Chord NACA0012 Aerofoil with Tappings (AF102)• Flat Plate Boundary Layer Model (AF106)

• Multi-Tube Manometer (AFA1)

• 150 mm Chord NACA2412 Aerofoil with Variable Flap (AF103)• Aircraft Model – Low Wing (AF107)• Aircraft Model – High Wing (AF108)

• Three-Component Balance (AFA3)

This table lists the instruments needed to performexperiments with the optional models if you do notrequire automatic data acquisition.

Recommended Ancillaries Page

TecQuipment makes many ancillaries for the windtunnel. These include optional models, instrumentsand extra or different instruments which you need towork with VDAS® for data acquisition.

Please refer to the tables below for full details ofwhich instruments you need for the different models.

Instruments:

• Versatile Data Acquisition System – 290Frame-mounted version (VDAS-F)

• Multi-Tube Manometer (AFA1) 14

• Basic Lift and Drag Balance (AFA2) 15

• Three-Component Balance (AFA3) 16

• Balance Angle Feedback Unit (AFA4) 17

• Differential Pressure Transducer (AFA5) 17

• 32-Way Pressure Display Unit (AFA6) 18

• Pitot-Static Traverse (300 mm) (AFA7) 19

• Smoke Generator (AFA10) 14

Models:

• Cylinder Model with Pressure Tapping (AF101) 20

• 150 mm Chord NACA0012 Aerofoil with Tappings 20(AF102)

• 150 mm Chord NACA2412 Aerofoil with Variable 21Flap (AF103)

• 150 mm Chord NACA0012 Aerofoils (AF104) 21

• 100 mm Diameter Flat Plate (AF105) 21

• Flat Boundary Layer Model (AF106) 21

• Aircraft Model – Low Wing (AF107) 21

• Aircraft Model – High Wing (AF108) 21

Subsonic Wind Tunnel Instruments and Accessories

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Multi-Tube Manometer (AFA1)

• Thirty-six tube tilting manometer formeasuring pressure taken from monitoringpoints on models in subsonic wind tunnels

• Uses water as manometer fluid withcolouring for ease of visibility

• Easy-to-read scale common to eachmanometer tube

• Preset incline levels for consistency andaccuracy – up to five times magnification

• Pressure reading level preset by adjustablefluid reservoir – includes fine-adjustmenthand-wheel

• Adjustable feet for precise set up

A 36-tube tilting manometer formeasuring pressure

A smoke generator and probe that allows students to see airflow in subsonic wind tunnels and other low flow rate airflow products.

It is a control unit that pumps oil to the tip of a probe. Alow-voltage electrical coil at the probe tip heats the oil toproduce a fine smoke trail. The smoke moves into the air

Produces a fine trace of smoke to allowstudents to see air flow in subsonic windtunnels and other air flow products

stream smoothly and steadily. Students can adjust thecontrols of the control unit to change the smoke strength tosuit the air flow conditions.

The apparatus includes an integral reservoir bottle. Low oilconsumption allows approximately six hours of use on onefilling of the bottle.

Supplied with instructions, smoke probe, spare heater tipand oil.




• Produces a smooth, fine trace of smoke

• Probe shaped to minimise wake generation

• Low oil consumption

• Fully adjustable smoke strength

• Supplied with smoke oil and spare heater tip

Smoke Generator (AFA10)

A 36-tube tilting manometer for measuring pressure onmodels in subsonic wind tunnels and fan test sets, includingTecQuipment’s AF100 series. A backboard with graduatedscale holds each manometer tube. For safety andconvenience, the manometer uses water as the manometer

fluid. This is via an adjustable reservoir with fine-adjust hand-wheel held at the side of the equipment. Water colouring isincluded to aid visibility.

The top of each manometer tube has a connection piece fortubing to connect to pressure tappings on the equipmentbeing monitored. The whole manometer tube assembly ismounted on a swivel. This allows it to be tilted in presetincrements to increase the sensitivity of measurement.Adjustable feet enable the whole apparatus to be preciselylevelled before use. The manometer is supplied withoperating instructions, a filling funnel and a spirit level.


• Differential Pressure Transducer (AFA5) 17



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1• Optional ancillary to TecQuipment’s modular

Subsonic Wind Tunnel (AF100)

• Single-component balance to measure liftand drag forces on models mounted in thetunnel

• Transmits the force on the model directly toa strain gauged load cell with digital display

• Fully compatible with TecQuipment’sVersatile Data Acquisition System (VDAS®) toenable accurate real-time data capture,monitoring and display on a computer

• Includes power supply

A single-component balance which measures the lift anddrag forces on models mounted in TecQuipment’s SubsonicWind Tunnel (AF100).

The balance mechanism enables test models with a rigidsupport arm to be mounted and held securely in position inthe working section of the wind tunnel. The arm transmitsthe force on the test model directly to a strain gauged loadcell. The load cell connects to a readout unit with a digitaldisplay, which is powered by a desktop power supply(included).

In addition, the equipment is fully compatible withTecQuipment’s optional Versatile Data Acquisition System(VDAS®) and can quickly and conveniently connect to aframe-mounting interface unit (VDAS-F, available separately).Using VDAS® enables accurate real-time data capture,monitoring, display, calculation and charting of all relevantparameters on a suitable computer (computer not included).

Measures lift and drag forces on modelsmounted in TecQuipment’s SubsonicWind Tunnel (AF100)

Basic Lift and Drag Balance (AFA2)

To measure the lift and drag forces on models (aerofoils forexample, available separately), the balance mounts on theside of the working section of the wind tunnel. The dragforce is measured first, then students rotate the balancemechanism through 90 degrees and repeat the test tomeasure the lift force. When mounted in the base of thewind tunnel working section, the balance measures the dragforce only. This is useful for a variety of investigations such aswind loadings on tall buildings. It can also be used tomeasure drag forces on model vehicles enabling students todetermine and compare coefficients of drag.

Note: For experiments requiring measurement of pitchingmoment as well as drag and lift forces, a three-componentbalance, such as TecQuipment’s AFA3, is required.


• Three-Component Balance (AFA3) 16

Base mounted with modelcar to measure drag

Shown fitted with theprotractor from the AF100Wind Tunnel

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EQUIPMENT TRAINING

We can offer a comprehensive equipment trainingprogramme that includes start-up, operation, shut-down, safety and maintenance procedures. Trainingprogrammes can be delivered at your premises or ourmanufacturing facility in the UK.


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Three-Component Balance (AFA3)

• Optional ancillary to TecQuipment’smodular Subsonic Wind Tunnel(AF100)

• Provides a convenient supportsystem for models to measure thelift, drag and pitching moment

• Fully compatible withTecQuipment’s Versatile DataAcquisition System (VDAS®) toenable accurate real-time datacapture, monitoring and display ona computer

• Digital display shows lift, drag and pitchingmoment directly

• Allows full adjustment of angle of incidenceof the model to direction of air flow

The Three-Component Balance fits onto the working sectionof TecQuipment’s Subsonic Wind Tunnel (AF100). It may alsobe used with other subsonic wind tunnels of similar design.

The Three-Component Balance provides an easy-to-usesupport system for wind tunnel models. It measures lift, dragand pitching moment exerted on the model.

The balance attaches to the vertical wall of the wind tunnelworking section. It is designed for air flows from right to leftwhen the balance is viewed from the front.

The balance comprises a mounting plate secured to the windtunnel working section. A triangular force plate is held on themounting plate by a mechanism that constrains it to move ina plane parallel to the mounting plate only, while leaving itfree to rotate about a horizontal axis. This arrangementprovides the necessary three degrees of freedom.

Models for use with the balance are available fromTecQuipment. Other models used with the equipment willneed a mounting stem. The forces acting on the model aretransmitted by cables to three strain gauged load cells. Theoutput from each load cell is taken via an amplifier to amicroprocessor-controlled display module. The displaymodule mounts onto the wind tunnel control andinstrumentation frame and includes a digital display to showthe lift, drag and pitching moment directly.

Measures lift, drag and pitchingmoment of models in TecQuipment’sSubsonic Wind Tunnel (AF100)

The equipment is fully compatible with TecQuipment’soptional Versatile Data Acquisition System (VDAS®) and canquickly and conveniently connect to a frame-mountinginterface unit (VDAS-F, available separately). Using VDAS®enables accurate real-time data capture, monitoring, display,calculation and charting of all relevant parameters on asuitable computer (computer not included).

The model support of the balance can be rotated by 360degrees. This allows adjustment of the angle of incidence ofthe model to the direction of air flow. The model support islocked in the required position by a simple clamp afteradjustment.

The Angle Feedback Unit (AFA4, available separately) fitsonto the Three-Component Balance and transmits therotational angle of the test model back to the automatic dataacquisition unit.


• Balance Angle Feedback Unit (AFA4) 17


• Basic Lift and Drag Balance (AFA2) 15

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Three-Component Balance shown with theAngle Feedback Unit (AFA4)


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Differential Pressure Transducer (AFA5)

• Optional ancillary to TecQuipment’s modularSubsonic Wind Tunnel (AF100)

• Measures and displays differential pressuresfrom models, Pitot-static tubes and otherdevices

• Quicker, easier and more versatile than usingliquid manometers

• Integral LCD allows direct pressuremeasurement

• Measures differential pressures or pressurewith respect to atmosphere


The Differential Pressure Transducer and readout is an optionalancillary to TecQuipment’s Subsonic Wind Tunnel (AF100). Itmeasures and displays pressures in Pitot-static tubes and otherpressure-sensing devices fitted to a wind tunnel, with respectto the atmosphere or differential pressures.

Microprocessor-controlled pressuremeasurement and display unit for use withTecQuipment’s Subsonic Wind Tunnel (AF100)

The control and instrumentation panel of the AF100 windtunnel includes a location for mounting up to twoDifferential Pressure Transducer modules. It ismicroprocessor-controlled and contains a calibrated pressuretransducer. The unit has an integral liquid crystal display thatallows the user to read pressure directly.

The signals of the pressure sensors may be output toTecQuipment’s optional Versatile Data Acquisition System(VDAS®). Using VDAS® enables accurate real-time datacapture, monitoring, display, calculation and charting of allrelevant parameters on a suitable computer (computernot included).

When the Differential Pressure Transducer is used with theautomatic data acquisition unit it provides a significantadvantage over conventional instruments such asmanometers. Many readings can be taken and the user mayuse a suitable spreadsheet software package to obtain amore accurate overview of pressure distributions.




Works withBalance Angle FeedbackUnit (AFA4)

The Balance Angle Feedback Unit is an optional ancillary foruse with TecQuipment’s Three-Component Balance (AFA3)to measure the angular position of models mounted on thebalance in TecQuipment’s Subsonic Wind Tunnel (AF100).The Balance Angle Feedback Unit mounts on the Three-Component Balance attached to the wind tunnel. It thentransmits the rotational angle of the model toTecQuipment’s Versatile Data Acquisition System (VDAS-F,not included). The angle of the model can then be loggedon a suitable computer (computer not included) along withother captured experimental data.

Measures angular positions of modelsmounted on TecQuipment’s Three-Component Balance (AFA3) with theVersatile Data Acquisition System (VDAS®)

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Note: The Balance Angle Feedback Unit can only be usedwith the Three-Component Balance (AFA3) and the VersatileData Acquisition System (VDAS®). The unit is supplied withan input board for VDAS®.


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32-Way Pressure Display Unit (AFA6)

• Optional ancillary to TecQuipment’s modularSubsonic Wind Tunnel (AF100)

• Measures and displays up to 32 differentialpressures from models, Pitot-static tubes andother devices

• Quicker, easier and more versatile than usingliquid manometers

• Integral LCD allows direct pressuremeasurement

• Measures pressures with respect toatmosphere


1The 32-Way Pressure Display Unit is an optional ancillary toTecQuipment’s modular Subsonic Wind Tunnel (AF100). Itmeasures and displays up to 32 different pressures frommodels, Pitot-static tubes and other measuring instrumentsfitted to a wind tunnel. It is ideally suited in applicationswhere multiple pressure measurements are required, forexample in boundary layer and tapped aerofoil modelinvestigations.

The unit mounts onto the control and instrumentation frameof the AF100 wind tunnel. The microprocessor-controlledunit contains 32 calibrated pressure transducers. Inputconnection to each of the pressure transducers is via quick-release pressure inputs mounted on the front panel of theunit. This allows easy and quick connection between the unitand an experiment mounted in a wind tunnel. All pressuresare measured with respect to atmosphere.

Microprocessor-controlled 32-way pressuremeasurement and display unit for use withTecQuipment’s Subsonic Wind Tunnel (AF100)

The unit has an integral liquid crystal display with a scrollswitch that allows all 32 channels to be viewed in groups offour at any time.

The conditioned outputs of the pressure sensors, and any otherconnected compatible electronic instruments, may be outputto TecQuipment’s optional Versatile Data Acquisition System(VDAS®) to allow computer-based data acquisition and display.Using VDAS® enables accurate real-time data capture,monitoring, display, calculation and charting of all relevantparameters on a suitable computer (computer not included).

When the 32-Way Pressure Display Unit is used with VDAS®it allows laboratory time to be used more efficiently becausedata can be captured and processed much more quicklythan when using manual techniques. The facility in thesoftware to average data to remove the fluctuations inherentin wind tunnel measurements, enhances the quality of theresults by making their interpretation much easier. Thisoption provides significant experimental advantages overconventional instruments such as manometers.



• Differential Pressure Unit (AFA5) 17

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Pitot-Static Traverse (300 mm)(AFA7)

• Optional ancillary to TecQuipment’sSubsonic Wind Tunnel (AF100)

• Mounts either upstream or downstream of atest model to measure pressures across the‘wake’ of a model

• Accurate digital display of position

• Zero facility allows the starting point of anexperiment to be set in any position

• Works with TecQuipment’s Versatile DataAcquisition System (VDAS®) to give accuratereal-time data capture, monitoring anddisplay on a computer

The Pitot-Static Traverse is an ancillary to TecQuipment’smodular Subsonic Wind Tunnel (AF100).

It is a Pitot-static tube which mounts in the working sectionof the wind tunnel, either upstream or downstream of theposition of the test model. This allows students to do ‘wake’traverses, downstream of a model. The vertical position ofthe tube, which is adjustable, is displayed on a digitalindicator.

The digital indicator position can be set to zero in anyposition. This allows the datum or starting point of anexperiment to be defined by the user.

A traversing Pitot-static tube with electronicposition measurement for use withTecQuipment’s Subsonic Wind Tunnel (AF100)

To display differential pressure, the Pitot-static tube connectsto a manometer supplied with the wind tunnel. Alternatively,pressures can be measured using one or more of thefollowing optional instruments:

• Multi-Tube Manometer (AFA1)

• Differential Pressure Unit (AFA5)

• 32-Way Pressure Display Unit (AFA6)

The pressure signals from the Pitot-Static Traverse may beoutput to TecQuipment’s optional Versatile Data AcquisitionSystem (VDAS®) to allow computer-based data acquisitionand display. Using VDAS® enables accurate real-time datacapture, monitoring, display, calculation and charting of allrelevant parameters on a suitable computer (computer notincluded). For pressure measurement this will require theoptional Differential Pressure Unit (AFA5) or 32-Way PressureDisplay Unit (AFA6).

Works with

Always here to HELP YOU

Whether you have a technical enquiry, need spareparts or support material you can contact ourCustomer Care team at:[email protected]


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Subsonic Wind Tunnel Models (AF101–AF108)

• Cylinder, aerofoils, flat plate and flat plate boundary layer models for use with TecQuipment’sSubsonic Wind Tunnel (AF100)

• Allow realistic and accurate experiments and demonstrations

• Simple, quick set-up and use

• Some models include pressure tappings for pressure distribution experiments

• All models work with the other optional instruments for the Subsonic Wind Tunnel

• High-quality surface-finish on all models for accurate results

Cylinder Model with Pressure Tapping(AF101)

A cylinder model that spans the full width of the workingsection of the Subsonic Wind Tunnel (AF100). A holder(included with the wind tunnel) supports the model in thetunnel. Also, the optional Three-Component Balance (AFA3,available separately) or the Single-Component Lift and DragBalance (AFA2, available separately) will support the model.

The model includes a single pressure tapping so, by rotatingthe model, students can find the pressure distributionaround the cylinder. TecQuipment offers several suitablepressure-measuring instruments (available separately).

Using a Pitot tube, students can traverse the model wake tofind the downstream pressure distribution and find the dragon the model. They can compare this to directmeasurements, obtained using a balance.

TecQuipment’s Smoke Generator (AFA10, not included)increases the educational value of the experiments byshowing the flow of air around the model.

A selection of optional models foruse with TecQuipment’s SubsonicWind Tunnel (AF100)

150 mm Chord NACA0012 Aerofoil withTappings (AF102)

The aerofoil has 20 static pressure tappings along its chordon the upper and lower surfaces. They each connect totubes that pass through the aerofoil and then out to clear,numbered, flexible tubes. Students can connect the tubes toother optional pressure-measurement instruments. They canthen measure the pressure distribution around the aerofoil,from which they can find the lift.

Using a Pitot tube, students can traverse the aerofoil wake tofind the downstream pressure distribution and find the dragon the aerofoil.

Students can compare these values of lift and drag withdirect measurements found from a balance. They can alsocompare them with the results from another aerofoil withthe same profile, such as the AF104 (see opposite page).Varying the angle of attack of the aerofoil with respect to theair stream allows students to find the changes to thepressure distribution. It also allows investigations into thecritical conditions at stall.



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150 mm Chord NACA2412 Aerofoil withVariable Flap (AF103)

An unsymmetrical section (cambered) aerofoil withadjustable flap. The adjustable flap allows students to studythe effects of control surfaces such as flaps, ailerons, elevatoror rudder. Students can also examine the difference betweenunsymmetrical and symmetrical aerofoils, by comparing theresults to the AF104 symmetrical aerofoils. The Three-Component Balance (AFA3, available separately) can holdthe aerofoil to measure lift, drag and pitching moment.

Using a Pitot tube, students can traverse the aerofoil wake tofind the downstream pressure distribution and find the dragon the aerofoil. They can compare these results with thedirect measurements from a balance.


150 mm Chord NACA0012 Aerofoils (AF104)

A set of two aerofoils. One aerofoil has a span that extendsthe full width of the working section of the Subsonic WindTunnel (AF100). This model has the characteristics of a two-dimensional aerofoil. The other aerofoil has a span thatextends for half of the working section of the wind tunnel.This model has the characteristics of a three-dimensionalaerofoil. Comparing the measured lift and drag of the twoaerofoils shows the differences between two-dimensionaland three-dimensional aerofoils.

Using a Pitot tube, students can traverse the aerofoil wake ofthe full-width aerofoil. This gives them the downstreampressure distribution to find the drag on the aerofoil. Theycan compare their results to direct measurements from abalance (available separately).

Students can compare the results from the full-width aerofoilwith the tapped aerofoil model (AF102, available separately)as it has the same (NACA0012) section.


100 mm Diameter Flat Plate (AF105)

This model shows the flow around a bluff body mountednormal to the air flow direction, and the drag force exertedon it.

A holder (included with the AF100 wind tunnel) supports themodel in the tunnel. Alternatively, either the optional Three-Component Balance (AFA3, available separately) or theSingle-Component Lift and Drag Balance (AFA2, availableseparately) can hold the model and measure the drag.


Flat Plate Boundary Layer Model (AF106)

Shows boundary layer development and separation.

The model is a flat plate that spans the full width of theAF100 wind tunnel working section. It has aerodynamicallyshaped blocks mounted across the plate at differentdistances from the leading edge. Each block has five tappingpoints at different heights along its leading edge. Eachtapping connects to flexible, numbered tubing that routesoutside the wind tunnel. Students can connect the tubes toother optional pressure-measurement instruments.

The tapping points allow students to measure the stagnationpressure. They use this to find the velocity at differentheights from the surface and at different distances from theleading edge. This allows students to find the growth of theboundary layer along the plate.

On the trailing edge of the plate is a hinged flap. Studentscan adjust the angles of both the plate and the flapindependently. This lets them create different arrangementsto control pressure distribution and the boundary layer.

The surface of the plate has small ‘tufts’ to help students seethe air flow around the surface of the plate.

Aircraft Model – Low Wing (AF107) Aircraft Model – High Wing (AF108)

Model aircraft with NACA profilewings. One has a low wingposition (bottom of thefuselage), the other has a highwing position (above thefuselage). These models aregood for experiments with lift,drag and pitching moment offixed wing aircraft.

Flight Demonstration Wind Tunnel (AF41)

Special Purpose Wind Tunnels

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• Gives students a safe, realistic introductionto the controls of a light aircraft

• Aircraft able to move vertically and pitchabout the quarter chord point independently

• Simulates take-off, level flight, cruise andlanding

• Demonstrations include aerofoil lift, stall,longitudinal stability and transient motion

• Includes electronic display of air speed,attitude, altitude, pressure and lift

• Tufts on the wing clearly demonstrate thephenomenon of separation and stall

• Brightly illuminated working section

• Adjustable centre of gravity of the model

• Optional smoke generator and chartrecorder (available separately)

For classroom demonstrations and student investigationsinto the behaviour of fixed-wing aircraft and wingperformance during take-off, flight and landing.

The apparatus is an open-circuit wind tunnel with a modelaircraft suspended in the working section. The model issupported by linkages that allow it to move vertically and topitch about the quarter chord point independently.

The working section is brightly illuminated and the aircraftmodel is clearly visible through a large transparent window.The operator flies the aircraft manually using a controlcolumn and throttle. These are positioned directly in front ofthe window and are arranged typically as found in a lightaircraft, providing realistic simulation of flight and the effectof the control surfaces.

To fly the aircraft, the operator pushes the throttle leverforward to increase the tunnel air speed. When the air speedreaches a certain level the aircraft may be made to ‘take-off’by drawing the control column slowly back. A digital displayshows air velocity (pressure) in the working section, attitude,altitude or lift force on the aircraft.

Continued on next page

Flight Demonstration WindTunnel (AF41)

A model aircraft suspended in an open-circuitwind tunnel. Includes realistic flight controls toteach a variety of principles of aircraft flight.


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1Air enters the working section through a flow straightener.The throttle controls the air speed in the tunnel byregulating an axial flow fan downstream of the workingsection. The change in air speed in the wind tunnel simulatesthe effect of increasing the change in air speed of a realaircraft due to a change in thrust from the propeller.

The control column is linked to the ‘all-flying’ tail plane ofthe aircraft. Pushing the column forward or pulling it backchanges the angle of the whole tail plane. A scale on thecontrol column indicates the tail plane angle. The controlcolumn differs from that of a normal aircraft in that it has nolateral control of the aircraft: it has no rudder on thetailplane and may only move up or down.

A locking control under the control column can lock theangle of the tail plane to any setting.

Small tufts cover the port wing of the aircraft. These showthe direction and quality of air flow over the wing surface, toshow separation and stall. Using the optional SmokeGenerator (AFA10, available separately) enhances flowvisualisation.

An adjustable weight allows the student to set the centre ofgravity of the model to different positions from fore to aft ofthe quarter chord point. A scale below the weight indicatesthe position. This enables students to derive the trim curvesand identify the neutral point.

To find the lift characteristic of the aerofoil, students link theaircraft to a load cell and vary the angle of attack.

Experiments

A variety of practical demonstrations, ‘hands-on’ flightsimulations, and student investigations into the behaviour offixed-wing aircraft and wing performance, including:

• Practical investigation of longitudinal stability and controlof the aircraft to demonstrate behaviour during take-off,level flight and landing.

• Determination of the effect of speed on attitude for levelflight and stall.

• Measurement of the lift curve for the wing up to andbeyond stall.

• Students can adjust the centre of gravity of the model toalter its trim. They can then plot trim curves anddetermine the neutral point.

With Two-Pen Chart Recorder (AF41a, availableseparately):

• Demonstration of phugoid motion in terms of altitude.

• Short period oscillation due to sudden disturbance can beshown by the change of incidence.

With Smoke Generator (AFA10, availableseparately):

• Visualisation of flow patterns past the aircraft’s aerofoiland tail plane.


• Two-Pen Chart Recorder (AF41a)

• Smoke Generator (AFA10) 14





Flight Demonstration Wind Tunnel (AF41)Continued from previous page

For moreinformationask for ourDATASHEETS

T +44 115 972 2611F +44 115 973 1520W www.tecquipment.comE [email protected]


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• High-quality, vertical windtunnel that helps studentsunderstand air flow arounddifferent shaped objects

• Ideal for small group experimentsor classroom demonstrations

• Includes smoke generator and lightingto show flow clearly

• Variable air speed

• Optional model sets with wide selectionof models available separately

A vertical, suction-type wind tunnel with smoke visualisation.Allows demonstrations and student investigations into theflow of air around a wide variety of different shaped models.

Ideal for small group experiments or classroomdemonstrations, the apparatus is floor standing. A variable-speed fan mounted on top of the wind tunnel produces the airflow through the working section. Air flow is vertically upwards.

A smoke generator connects to a comb mounted in the windtunnel below the working section. Students can move thecomb from side to side to aid investigations into theaerodynamic properties of a test model. Smoke is producedby the vapourisation of a high-quality food-grade oil. A filterhelps provide uniform air flow. The smoke is non toxic.

The front wall of the working section of the wind tunnel istransparent and removable. This enables users to easily andquickly attach the optional models to the back of theworking section. It also allows a clear view of the smoketrails. Test model sets for the wind tunnel are availableseparately (AF80a and AF80b). Lamps illuminate theworking section from both sides to improve the visibility ofthe smoke.

The wind tunnel is held on a metal frame fitted with castorsfor mobility. A control unit on the frame contains thecontrols for the fan speed.

Experiments

When used with the optional models, the visualisation anddemonstration of:

• Boundary layers

• Separation

• Rotational flow

Essential Ancillaries

• Model Set (AF80a), including:

– Aerofoil– Circular cylinder– Sphere– Slotted orifice– Disc– Circular orifice– Hemisphere– Wing tip– ISA nozzle– Model car and truck

Recommended Ancillaries

• Additional Model Set (AF80b), including:

– Bend– Cascade corner– Plain corner– Heat exchanger tube bank





Uses smoke trails to showair flow around differentshaped models

Photograph of the smoketrails around a hemisphere

Flow Visualisation WindTunnel (AF80)

Supersonic Nozzle

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Nozzle Flow Apparatus (AF27)

• Practical laboratory apparatus whichdemonstrates the thermodynamics and fluidmechanics of the adiabatic expansion of airthrough subsonic and supersonic nozzles

• Convenient size, floor-standing

• Includes three interchangeable, profiled andpolished brass nozzles

• Battery-powered digital instrumentation

• Built-in instrument panel and studentworktop

• High levels of safety

Demonstrates the thermodynamics and fluid mechanics ofthe adiabatic expansion of air through subsonic andsupersonic nozzles.

The apparatus is floor standing. It comprises a pressure chestwith a removable lid and a pressure regulator at its input anda throttling valve at its output. The equipment includes threeinterchangeable, profiled and polished brass nozzles. Onenozzle fits onto the chest at any one time. Each nozzleincludes a mimic panel clearly showing the nozzle profile.The nozzles and the mimic panels have a safe and securestorage position when not in use.

Compressed air from an external source (not included)enters the pressure chest and passes through the nozzle. Thesettings of the inlet pressure regulator and the throttlingvalve determine the operating pressure of the chest as wellas the inlet pressure/outlet pressure ratio of the nozzle.

A stainless-steel probe on a manually adjustable, verticaltraverse measures the pressure distribution along the axis of

the nozzle. The traverse assembly includes a digital depthindicator to measure the probe position in the nozzle. Theselected nozzle’s mimic panel mounts adjacent to the probetraverse to give a visual indication of the position of theprobe in the nozzle during experiments.

The air discharge from the nozzle passes along a longhorizontal parallel pipe before being discharged toatmosphere. An orifice plate in the pipe includes twopressure tappings which connect to an inclined manometerto allow the air flow to be determined.

A sturdy steel frame with an instrument panel and studentworktop holds the main assembly. The instrument panelincludes an inclined manometer, and gauges to display chestand probe pressures. Air temperature is displayed digitally.

Experiments

• The relationship between pressure ratio and flow forconvergent and convergent/divergent Laval nozzles

• The pressure profile in convergent/divergent nozzles atvarious pressure ratios

• Investigation of expansion with friction in a parallelpassage at high subsonic velocities

• Boundary layer growth under subsonic and supersonicconditions

• The phenomenon of choked flow corresponding to sonicvelocity at a nozzle throat

Essential Ancillaries

• Compressor (AF27a)


• Supersonic Wind Tunnel – Intermittent (AF300) 27

• Supersonic Wind Tunnel – Continuous (AF302) 30

Demonstrates the thermodynamics and fluid mechanics of the adiabatic expansion of air through subsonic and supersonic nozzles

Supersonic Wind Tunnels

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Intermittent Supersonic Wind Tunnel (AF300)

• Laboratory-scale wind tunnel for subsonicand supersonic tests, up to Mach 1.8

• Compact design – does not need largelaboratory space

• Supplied with aerodynamic models forsupersonic tests – includes model angle-feedback encoder

• Works with TecQuipment’s Versatile DataAcquisition System (VDAS®) for instantrecording of multiple readings andautomatic calculations

• Electronic instruments measure and displaymultiple pressures at the same time, for easeof use and for connection to VDAS®

• Supplied with set of different liners forcontrolled subsonic and supersonic air flow

• Induction flow for better air flow andaccurate results

An intermittent operation, induction-type supersonic windtunnel for investigations into subsonic and supersonic flow.This includes tests on the flow around two-dimensionalmodels at subsonic and supersonic air speeds.

A compressed air supply (AF300b, available separately)induces a flow in the working section of the wind tunnel.This gives a less turbulent and more stable flow for accurateresults and comparison with theory. The optionalcompressed air supply includes filters and air dryers to give adust-free and dry air source needed for good results.

Students use a delivery valve to allow compressed air toenter the wind tunnel. The wind tunnel includes two

Investigates subsonic and supersonicair flow, including flow around two-dimensional models

Screenshot of the optional

VDAS® software

Shown withthe optionalSchlierenApparatus(AF300a)

Works with

Continued on next page


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analogue pressure gauges. One measures the compressed airpressure available from the supply (for reference); the othermeasures the pressure delivered to the wind tunnel andincludes an electronic transducer that connects toTecQuipment’s Versatile Data Acquisition System (VDAS®) torecord the pressure.

The working section of the wind tunnel is a convergent-divergent nozzle with a removable top part (‘liner’). Theshape of the liner controls the maximum air velocity at thedivergent part of the working section. Included are threedifferent liners.

High optical-quality glass windows (‘portals’) are at each sideof the divergent part of the working section. The portalsallow students to use the optional Schlieren Apparatus(AF300a, available separately). This allows display andrecording of images of pressure waves around two-dimensional models.

Included is a set of two-dimensional models. These mountbetween the portals inside the working section. Students canadjust the angle of the models. An encoder electronicallymeasures the model angle.

Spaced at precise intervals along the working section of thewind tunnel are pressure tappings. Two extra tappingsconnect to one of the models when in use. A 32-waypressure display (included) connects to all the pressuretappings. It displays the pressures and transmits them toVDAS® for instant recording and calculations of pressureratios and Mach numbers.

Included is a bench-mounting instrument frame that holdsand provides power for the electronic instruments and theVDAS® interface unit. The instrument frame connects to asuitable electrical supply.

VDAS® allows accurate real-time data capture, monitoring,display, calculation and charting of all the importantreadings on a suitable computer (computer not included).

Experiments

• Pressure distribution along a convergent/divergent(Laval) nozzle with subsonic and supersonic air flow

• Comparison of theoretical and actual pressure distribution

• Comparison of actual and theoretical area ratio of anozzle at supersonic air velocities (Mach numbers)

• Pressures around a two-dimensional model in subsonicand supersonic flow conditions, at different angles ofincidence

• Lift coefficient for aerodynamic models in supersonic flow

• Shock waves and expansion patterns around a two-dimensional model in supersonic flow conditions (whenused with the optional Schlieren Apparatus).

Essential Ancillaries Page

• Air Compressor Receiver and Dryer (AF300b)



• Schlieren Apparatus (AF300a) 29



• Nozzle Flow Apparatus (AF27) 26

• Continuous Supersonic Wind Tunnel (AF302) 30

Intermittent Supersonic Wind Tunnel (AF300)Continued from previous page

Capture the power of VDAS®

the versatile data acquisition system from TecQuipmentOur Versatile Data Acquisition System is a highly effective way of collecting and using data from experimentsusing TecQuipment educational teaching products.

LOOK AT THE BENEFITS...

VERSATILE – can be used across a wide range of TecQuipment products

DATA – transforms raw data instantly which easily exports or creates sophisticated graphs and tables

ACQUISITION – USB connectivity, multiple-source real-time data capture

SYSTEM – an expandable modular approach providing easy-to-use digital plug-and-play technology

VDAS® is the most up-to-date, effective data acquisition system currently available for education. There are othersolutions on the market, but none which offer the convenience, functionality or wide range of features andbenefits of TecQuipment’s Versatile Data Acquisition System.

Visit our website at www.tecquipment.com for more information

Capture the power of VDAS®

the versatile data acquisition system from TecQuipmentOur Versatile Data Acquisition System is a highly effective way of collecting and using data fromexperiments using TecQuipment educational teaching products.

LOOK AT THE BENEFITS...

VERSATILE – can be used across a wide range of TecQuipment products

DATA – transforms raw data instantly which easily exports or creates sophisticated graphs and tables

ACQUISITION – USB connectivity, multiple-source real-time data capture

SYSTEM – an expandable modular approach providing easy-to-use digital plug-and-play technology

VDAS® is the most up-to-date, effective data acquisition system currently available for education. Thereare other solutions on the market, but none which offer the convenience, functionality or wide range offeatures and benefits of TecQuipment’s Versatile Data Acquisition System.

Visit our website at www.tecquipment.com for more information


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Schlieren Apparatus (AF300a)

• Monochrome Schlieren apparatuswith a high-power light source andimaging screen

• High-quality, laboratory-standardmirrors and lenses for clear imageswithout distortion

• Shows supersonic air flow patternsaround models

• Shows shockwaves and expansions

• Includes digital imaging equipmentand TV monitor

Schlieren apparatus for use withTecQuipment’s IntermittentSupersonic Wind Tunnel (AF300)

A monochrome Schlieren apparatus for use with theIntermittent Supersonic Wind Tunnel (AF300).

The Schlieren apparatus allows students to see densitygradients as variations in intensity of illumination. Thisallows them to see supersonic air flow patterns aroundmodels. It also clearly shows shockwaves and expansions,and students can compare their position and angle withvalues predicted by theory.

The mirrors and lenses are of high optic standards to reduceany possibility of optic distortions of the images.

The apparatus includes digital imaging equipment to recordthe images; this is useful when using an intermittentsupersonic wind tunnel.

The TV monitor is particularly useful to display the imagesto groups of students. The imaging equipment can capturestill images and any real-time changes in the image.

The RIGHT part in theRIGHT place at theRIGHT time

We have invested in a computerised stock control systemto manage the 40,000 different components, getting theproduct and the parts to you quickly ensuring alldeliveries are met.

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Continuous Supersonic Wind Tunnel (AF302)

• A suction-type continuous-operationsupersonic wind tunnel for investigationsinto two-dimensional air flow around modelsfor air speeds up to Mach 1.8

• Includes high-quality optical glass windowsin the working section, suitable for use withan optional Schlieren system

• Includes a selection of models for two-dimensional flow experiments and anencoder for feedback of model angle

• Supplied with a multi-pressure display unitand calibrated pressure sensors to showpressures relative to atmosphere

• Includes a remote-control for the vacuumpump for ease of use

• Works with TecQuipment’s Versatile DataAcquisition System (VDAS®) for automaticdata acquisition

A suction-type, continuous-operation supersonic windtunnel for investigations into subsonic and supersonic airflow. It also allows students to study air flow in twodimensions around aerodynamic models.

An instrument frame (supplied) holds a remote-control unitthat controls a high-capacity vacuum pump. The pumpcreates a low pressure downstream of the working section todraw air into the wind tunnel. A bypass duct with a hand-operated valve allows the operator to reduce the air flowthrough the working section without disturbing the qualityof the main air flow. This is useful for startup and shutdownand for subsonic tests.

The working section of the wind tunnel is a convergent-divergent nozzle with a removable top part (‘liner’). Theshape of the liner controls the maximum air velocity at thedivergent part of the working section. Included are threedifferent liners.

For investigations into flow aroundtwo-dimensional models at supersonicand subsonic air speeds

Screenshot of theVDAS® software

Works with


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A selection of models is included with the equipment (onehas pressure tappings) for experiments in two-dimensionalflow. These fit in the ‘portal’ of the working section, flush toboth windows. A geared mechanism allows students toadjust the incidence angle of the models. An encoder workswith TecQuipment’s Versatile Data Acquisition System(VDAS®) to measure the model angle.

Pressure tappings along the working section connect to a‘mimic’ panel and multi-pressure display unit in theinstrument frame. The display unit shows the pressures atthe tappings. The display includes calibrated pressuresensors to measure pressures relative to atmosphere. It alsoshows the pressures on one of the models.

An analogue pressure gauge measures and displays thesuction of the pump (tunnel reference pressure). Thispressure line also connects to the multi-pressure display fordata acquisition.

The equipment works with VDAS® and can quickly andconveniently connect to a frame-mounting interface unit(VDAS-F, not included). Using VDAS® enables accurate real-time data capture, monitoring, display, calculation andcharting of all relevant parameters on a suitable computer(computer not included).

The wind tunnel includes transparent windows in theworking section. These are high-quality optical glass suitablefor use with the optional Schlieren Apparatus (AF302a,available separately) enabling display and recording ofimages of high-speed flow.

Experiments

• Pressure distribution along a convergent/divergent(Laval) nozzle with subsonic and supersonic air flow

• Comparison of theoretical and actual pressuredistribution

• Comparison of actual and theoretical area ratio of anozzle at supersonic air velocities (Mach numbers)

• Pressures around a two-dimensional model in subsonicand supersonic flow conditions, at different angles ofincidence

• Lift coefficient for aerodynamic models in supersonic flow

• Shock waves and expansion patterns around a two-dimensional model in supersonic flow conditions (whenused with the optional Schlieren Apparatus)

Essential Ancillaries Page



• Schlieren Apparatus AF302a 31



• Nozzle Flow Apparatus (AF27) 26

• Intermittent Supersonic Wind Tunnel (AF300) 27

Schlieren Apparatus (AF302a)

• Monochrome Schlieren apparatuswith high-power light source andimaging screen

• High-quality, laboratory-standardmirrors and lenses for clear imageswithout distortion

• Shows supersonic air flow patternsaround models

• Shows shockwaves and expansions

• Includes digital imaging equipmentand TV monitor

Schlieren apparatus for use withTecQuipment’s ContinuousSupersonic Wind Tunnel (AF302)

A monochrome Schlieren apparatus for use with theContinuous Supersonic Wind Tunnel (AF302).

The Schlieren apparatus allows students to see densitygradients as variations in intensity of illumination. This allowsthem to see supersonic air flow patterns around models. Italso clearly shows shockwaves and expansions, and studentscan compare their position and angle with values predictedby theory.

The mirrors and lenses are of high optic standards to reduceany possibility of optic distortions of the images.

The apparatus includes digital imaging equipment to recordthe images. The TV monitor is useful to display the images togroups of students. The imaging equipment can capture stillimages and any real-time changes in the image.


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1TecQuipment Document Packs– making it clear for the customer

We send document packs with all TecQuipment manufactured products.

Document packs contain:

• a packing contents list (PCL) toshow you what parts we pack withthe product;

• a test certificate to show you thatwe’ve thoroughly tested theproduct before we send it to you;

• user guides* and safetyinformation to show you how touse the product safely and learnhow it works.

Some packs also include compact discs (CD-ROMs) with TecQuipment software (for example, VDAS®).

At TecQuipment we continually improve our user guides so they include pictures of the products, cleardiagrams and plain English text. This helps you to understand the product more clearly. Where necessary,the guides include theory, suggested experiments and typical results to help students understand whatthe product teaches.

*Some products may not need user guides, as their details are already shown in their parent product, for example the optional

pumps on the MFP103.

01 aerodynamics 2012

Documents

flow visualisation wind

supersonic flow

wind tunnelsthe quality

supersonic nozzle

flow of air

highqualitywind tunnel

wide range of features

modular air flow bench