TA300/300 Tunnel aérodynamique, 300 x 300 mm

8.6.- AÉRODYNAMIQUE
AERODYNAMIC TUNNEL, 300 X 300 MM - TA300/300

SYSTEMES INNOVANTS

The Aerodynamic Tunnel, 300 x 300 mm, "TA300/300", is a wind tunnel designed to study subsonic aerodynamics in a tunnel in opencircuit and with incompressible subsonic flow.

Voir description générale

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Description Générale

The Aerodynamic Tunnel, 300 x 300 mm, "TA300/300", 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 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 9.5:1 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 PMMA 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. An electronic console contains the controller for the axial fan.

There are sixty different appropriate tappings for the pressure takings (along the tunnel and in the different models). The unit includes a twenty tube water manometer to measure the static pressure.

The models are mounted on a circular hatch, 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.

Des exercices et pratiques guidées

EXERCICES GUIDÉS INCLUS DANS LE MANUEL

  1. Comprehensive study of subsonic aerodynamics and airflow studies.
  2. Study of flow visualization.
  3. Study of static pressure, dynamic pressure and total pressure using a Pitot’ tube.
  4. Study of velocity measurement using a Pitot tube.
  5. Flux in a nozzle: Determination of the characteristics of the pressures field in a nozzle.
  6. 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.
  7. Sensors calibration.

PLUS D'EXERCICES PRATIQUES À EFFECTUER AVEC CETTE ÉQUIPEMENT

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

  1. Display of flows around different drag models:
  • Sphere Drag Model (TA1/300).
  • Drag Model of Hemisphere Convex to Airflow (TA2/300).
  • Circular Plate Drag Model (TA3/300).
  • Ring Drag Model (TA4/300).
  • Square Plate Drag Model (TA5/300).
  • Cylinder Drag Model (TA6/300).
  • Streamlined Shape Drag Model (TA7/300).
  • Paraboloid Drag Model (TA8/300).
  • Drag Model of Hemisphere Concave to Airflow (TA9/300).
  • Wing with Flaps Drag Model (TA10/300).
  • Flag Drag Model (TA11/300).
  • Wing Model with NACA 0015 Profile (TA12/300).
  • Wing Model with NACA 54118 Profile (TA13/300).
  • Wing Model with NACA 4415 Profile (TA14/300).
  • Dimpled Sphere Drag Model (TA15/300).
  1. Determination of the drag coefficient and the lift coefficient in different models:
  • Sphere Drag Model (TA1/300).
  • Drag Model of Hemisphere Convex to Airflow (TA2/300).
  • Circular Plate Drag Model (TA3/300).
  • Ring Drag Model (TA4/300).
  • Square Plate Drag Model (TA5/300).
  • Cylinder Drag Model (TA6/300).
  • Streamlined Shape Drag Model (TA7/300).
  • Paraboloid Drag Model (TA8/300).
  • Drag Model of Hemisphere Concave to Airflow (TA9/300).
  • Wing with Flaps Drag Model (TA10/300).
  • Flag Drag Model (TA11/300).
  • Wing Model with NACA 0015 Profile (TA12/300).
  • Wing Model with NACA 54118 Profile (TA13/300).
  • Wing Model with NACA 4415 Profile (TA14/300).
  • Dimpled Sphere Drag Model (TA15/300).
  1. Measurement of drag forces and lift forces in different models:
  • Sphere Drag Model (TA1/300).
  • Drag Model of Hemisphere Convex to Airflow (TA2/300).
  • Circular Plate Drag Model (TA3/300).
  • Ring Drag Model (TA4/300).
  • Square Plate Drag Model (TA5/300).
  • Cylinder Drag Model (TA6/300).
  • Streamlined Shape Drag Model (TA7/300).
  • Paraboloid Drag Model (TA8/300).
  • Drag Model of Hemisphere Concave to Airflow (TA9/300).
  • Wing with Flaps Drag Model (TA10/300).
  • Flag Drag Model (TA11/300).
  • Wing Model with NACA 0015 Profile (TA12/300).
  • Wing Model with NACA 54118 Profile (TA13/300).
  • Wing Model with NACA 4415 Profile (TA14/300).
  • Dimpled Sphere Drag Model (TA15/300).
  1. Study of pressure and flow distribution around a model:
  • Pressure Distribution in a Wing Model with NACA 0015 Profile (TA19/300).
  • Pressure Distribution in a Wing Model with NACA 54118 Profile (TA20/300).
  • Pressure Distribution in a Wing Model with NACA 4415 Profile (TA21/300).
  • Pressure Distribution in a Cylinder (TA22/300).
  1. Study of effect of changing in Bernoulli Apparatus Model (TA23/300) the cross section and application of the Bernoulli equation.
  2. Investigation into the influence of models shape in the drag forces (Drag Models and Force Measurement Console and Sensors (TA300/300-TAR)).
  3. Study of static pressure, dynamic pressure and total pressure using a Pitot tube (TA17/300).
  4. Study of Boundary Layer in a Flat Plate (TA300/300-BLE).
  5. Demonstration of flow patterns around different objects with the Smoke Generator (TA300/300-SG1).
  6. Study of static pressure, dynamic pressure and total pressure with the Wake Survey Rake (TA18/300).
  7. Study of fluter (TA24/300).
  8. Study of the Accessory for Particle Image Velocimetry (APIV).

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8.6.- AÉRODYNAMIQUE
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