TA50/250C Windkanal, 50 x 250 mm, computergesteuert.

8.6.- AERODYNAMIK
COMPUTER CONTROLLED AERODYNAMIC TUNNEL, 50 X 250 MM - TA50/250C

Unit: TA50/250C. Computer Controlled Aerodynamic Tunnel, 50 x 250 mm

COMPUTER CONTROLLED AERODYNAMIC TUNNEL, 50 X 250 MM - TA50/250C

TA50/250C/CIB. Control Interface Box: The Control Interface Box is part of the SCADA system

COMPUTER CONTROLLED AERODYNAMIC TUNNEL, 50 X 250 MM - TA50/250C

Process diagram and unit elements allocation

COMPUTER CONTROLLED AERODYNAMIC TUNNEL, 50 X 250 MM - TA50/250C

TA50/250C/SOF. TA50/250C Software. Main Screen

COMPUTER CONTROLLED AERODYNAMIC TUNNEL, 50 X 250 MM - TA50/250C
COMPUTER CONTROLLED AERODYNAMIC TUNNEL, 50 X 250 MM - TA50/250C
COMPUTER CONTROLLED AERODYNAMIC TUNNEL, 50 X 250 MM - TA50/250C
COMPUTER CONTROLLED AERODYNAMIC TUNNEL, 50 X 250 MM - TA50/250C

INNOVATIVE SYSTEME

The Computer Controlled Aerodynamic Tunnel, 50 x 250 mm, "TA50/250C", is a wind tunnel designed to study subsonic aerodynamics in a tunnel in open circuit and with incompressible subsonic flow.

Allgemeine Beschreibung anzeigen

Erweiterungen

ICAI

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FSS

Fehlersimulationssystem
PLCHMI

Lokale/Remote IIoT-Steuerung und -Überwachung mit HMI
ESN

EDIBON Scada-Net Systeme
ECL

EDIBON Cloud Lernen

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ALLGEMEINE BESCHREIBUNG

The Computer Controlled Aerodynamic Tunnel, 50 x 250 mm, "TA50/250C", is a wind tunnel designed to study subsonic aerodynamics in a tunnel in open circuit and with incompressible subsonic flow. Air is drawn by a variable speed fan, computer controlled, located at the discharge end of the tunnel. Several models and accessories are available, allowing a comprehensive study of subsonic aerodynamics.

The unit includes several tunnel sections. In the same order in which the flow crosses them, they are: lips, haven section, contraction, working area, diffuser and fan.

Lips and a haven section are incorporated at the tunnel inlet to reduce the pressure drop and the interferences in the flow. An 8:1 contraction ratio and a perfectly studied contour curve of the contraction ensures well developed airflow through the working area.

The working area is located after the contraction. It is a constant section tract, where the models to be tested are assembled, and the dimensions of the transverse section is bigger than the models. It is made of clear acrylic resin to allow to observe the models. This section includes a Pitot static tube in the top side to study the static pressure, dynamic pressure and total pressure.

A diffuser is included at the tunnel outlet to avoid the generation of turbulences, which can generate damages in the current quality at the working area.

An axial-flow fan, located at the discharge end of the tunnel, provides a more uniform velocity profile at the working area.

There are sixty different appropriate tappings for the pressure takings (along the tunnel and in the different models). The unit includes thirty differential pressure sensors to measure the static pressure.

The models are mounted on a circular hatch (200 mm), and they are coupled to the working area to seal the opening. They are secured by knobs on the side wall of the working area.

This Computer Controlled Unit is supplied with the EDIBON Computer Control System (SCADA), and includes: The unit itself + a Control Interface Box + a Data Acquisition Board + Computer Control, Data Acquisition and Data Management Software Packages, for controlling the process and all parameters involved in the process.

ÜBUNGEN UND GEFÜHRTE PRAKTIKEN

GEFÜHRTE PRAKTISCHE ÜBUNGEN IM HANDBUCH ENTHALTEN

  1. Comprehensive study of subsonic aerodynamics and airflow studies.
  2. Measurement of pressure distribution around a two dimensional body.
  3. Study of flow visualization.
  4. Study of static pressure, dynamic pressure and total pressure using a Pitot' tube.
  5. Study of velocity measurement using a Pitot tube.
  6. Flux in a nozzle: Determination of the characteristics of the pressures field in a nozzle.
  7. Flux in a nozzle: Observation of the local characteristics, depending on whether the walls have a curvature or not, as well as what happens at the inlet and outlet areas of the contraction.
  8. House Scale Model (TA1): Study of aerodynamic forces due to the wind on a house.
  9. House Scale Model (TA1): Determination of the aerodynamic loads generated by the wind on a house walls.
  10. Cylinder Model (TA2): Study of flow around a cylinder.
  11. Cylinder Model (TA2): Determination of the form of the pressures field around a cylinder on which a current perpendicular to the axis impacts.
  12. Cylinder Model (TA2): Determination, by the type of detachment, whether the boundary layer finally becomes turbulent or remains laminar.
  13. Cylinder Model (TA2): Determination of the resistance coefficient of the cylinder.
  14. Cylinder Model (TA2): Relation of all the above-mentioned with the Reynolds's number.
  15. Convex Semi-Cylinder Model (TA3): Study of flow around a convex semi-cylinder.
  16. Convex Semi-Cylinder Model (TA3): Determination of the field of pressures in the convex semi-cylinder.
  17. Convex Semi-Cylinder Model (TA3): Determination of the aerodynamic resistance coefficients in the convex semi-cylinder.

MEHR PRAKTISCHE ÜBUNGEN FÜR DAS GERÄT

  1. Sensors calibration.

Additional practical possibilities to be done with the Optional Models and Accessories: (Not included)

  1. Study of aerodynamic forces due to the wind on a Car Model (TA4).
  2. Study of aerodynamic forces due to the wind on a Lorry Model (TA5).
  3. Study of aerodynamic forces due to the wind on a Lorry with Wind Deflector Model (TA6).
  4. Study of aerodynamic forces due to the wind on a Plane Model (TA7).
  5. Study of aerodynamic forces due to the wind on a Train Model (TA8).
  6. Study of aerodynamic forces due to the wind on a Projectile Model (TA9).
  7. Study of aerodynamic forces due to the wind on a Circular Disc Model (TA10).
  8. Study of aerodynamic forces due to the wind on a Wing of a Plane Model (TA11).
  9. Study of flow and pressure distribution around a Wing of a Plane Model (TA11) at different angles of attack.
  10. Study of aerodynamic forces due to the wind on a Concave Semi-Cylinder Model (TA12).
  11. Study of aerodynamic forces due to the wind on a Blunt Element Model (TA13).
  12. Study of effect of changing in Bernoulli Apparatus Model (TA14) the cross section and application of the Bernoulli equation.
  13. Study of laminar and turbulent boundary layer development with the Boundary Layer Plate Model (TA15) and the Boundary Layer Experiment Accessory (TA50/250-BLE).
  14. Study of static pressure, dynamic pressure and total pressure with the Wake Survey Rake (TA17).
  15. Study of aerodynamic forces due to the wind on a Streamlined Shape (TA18).
  16. Investigation into the influence of models shape in the drag forces (Lift and Drag Balance (TA19), Drags Models (TA20) and Forces Measurement Interface (TA50/250C-TARC)).
  17. Demonstration of flow patterns around different objects with the Smoke Generator (TA50/250-SG1).

Other possibilities to be done with this Unit:

  1. Many students view results simultaneously. To view all results in real time in the classroom by means of a projector or an electronic whiteboard.
  2. Open Control, Multicontrol and Real Time Control. This unit allows intrinsically and/or extrinsically to change the span, gains, proportional, integral, derivative parameters, etc, in real time.
  3. The Computer Control System with SCADA and PID Control allow a real industrial simulation.
  4. This unit is totally safe as uses mechanical, electrical and electronic, and software safety devices.
  5. This unit can be used for doing applied research.
  6. This unit can be used for giving training courses to Industries even to other Technical Education Institutions.
  7. Control of the TA50/250C unit process through the control interface box without the computer.
  8. Visualization of all the sensors values used in the TA50/250C unit process.
  9. By using PLC-PI additional 19 more exercises can be done.
  10. Several other exercises can be done and designed by the user.

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