SUBSONIC WIND TUNNEL 600mm
An open circuit suction subsonic wind tunnel with a working section of 450 mm by 450 mm and 1000 mm long. Package includes the Aerofoil with Tappings, a Three-Component Balance, two Differential Pressure Transducers, a 32-Way Pressure Display Unit and data acquisition (VDAS-F).
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A compact, practical open-circuit suction wind tunnel for studying aerodynamics. The wind tunnel saves time and money compared with full-scale wind tunnels or airborne laboratories.
The wind tunnel gives accurate results and is suitable for undergraduate study and research projects.
Air enters the tunnel through an aerodynamically designed effuser (cone) that accelerates the air linearly. It then enters the working section and passes through a grill before moving through a diffuser and then to a variable-speed axial fan. The grill protects the fan from damage by loose objects. The air leaves the fan, passes through a silencer unit and then back out to atmosphere.
A separate control and instrumentation unit controls the speed of the axial fan (and the air velocity in the working section).
A metal frame supports the wind tunnel. The frame includes lockable castors for convenient mobility.
Included with the wind tunnel:
- Three-Component Balance (AF1450T)
- NACA 0012 Aerofoil with Tappings (AF1450B)
- A 150 mm chord 300 mm span NACA0012 aerofoil with pressure tappings.
- Differential Pressure Display (AF1450V) x 2
- Measures and displays pressures with respect to the atmosphere or differential pressures.
- 32-Way Pressure Display Unit (AF1450W)
- Measures and displays up to 32 different pressures from models, Pitot-static tubes and other measuring instruments ﬁtted to the wind tunnel.
- Versatile Data Acquisition System (VDAS-F)
- A frame mounting versatile data acquisition system (VDAS®) to allow computer-based data capture.
A wide variety of subsonic aerodynamics experiments (some need ancillaries), including:
- Flow past bluff and streamlined bodies with pressure and velocity observations in the wake
- Investigations into boundary layer development
- Inﬂuence of aspect ratio on aerofoil performance
- Performance of an aerofoil with ﬂap, inﬂ uence of ﬂap angle on lift, drag and stall
- Pressure distribution around a cylinder under sub- and super-critical ﬂ ow conditions
- Study of characteristics of models involving basic measurement of lift and drag forces
- Study of the characteristics of three-dimensional aerofoils involving measurements of lift, drag and pitching moment
- Study of the pressure distribution around an aerofoil model to derive the lift, and comparison with direct measurements of lift
- Drag force on a bluff body normal to an air ﬂow
- Flow visualisation
The electronic and aeronautical test facility at Milton Keynes College, UK recently purchased an AF1300 Subsonic Wind Tunnel for the teaching of the Level 3 Aeronautical Engineering BTEC Diploma students, which is used on a regular basis as part of the course.
Un conjunto de arranque formado por el Túnel de Viento Subsónico AF1300, Levantamiento Básico y el Equilibrio de Resistencia AF1300Z y un conjunto Tridimensional de Modelos de Resistencia AF1300J.
The high wing model aircraft with NACA profile wings for use with the Large Subsonic Wind Tunnel (AF1600) is good for experiments with lift, drag and pitching moment of fixed wing aircraft.
A set of different shape models for use with the Large Subsonic Wind Tunnel (AF1600S) each with identical frontal area to allow students to compare the different coefficient of drag for each shape. Includes a dummy stem for tests to cancel out the drag due to each model’s support arm.
A 150mm chord NACA2412 aerofoil with 590 span featuring a variable flap that adjusts +/- 90 degrees for use with the AF1600 Subsonic Wind Tunnel.
A cylinder model that spans the full width of the working section of the AF1600S Subsonic Wind Tunnel. A holder (included with the wind tunnel) supports the model in the tunnel.
This smoke generator and probe are an optional ancillary to TecQuipment's AF1125, AF1450 and AF1600. It allows the observation of airflow in subsonic wind tunnels and other airflow situations.