DESCRIPTION The C30 – Computer Controlled Wind Tunnel enables the user to carry out advanced studies in the Aerodynamics fields including boundary layer experiments, flow visualisation, pressure distribution, study of turbulence and offering the possibility of developing self-design aerodynamics profiles to be tested. The wind tunnel comprises outstanding features such as computer control, remote operation, datalogging and diagrams plotting in real time. The system also benefits from clear visualisation of every model under test due to the architecture of the working section in transparent material and the compact design of all components. TECHNICAL SPECIFICATIONS A stand-alone computer controlled subsonic wind tunnel for conducting experiments in aerodynamics The wind tunnel is mounted on a steel base on wheels for mobility Working section of 310mm by 310mm and 660mm long The unit operates as an open circuit system Inverter controlled AC suction fan to drag the air flow through the working section Accurate speed control up to 40m/s The duct incorporates a honeycomb flow straightener to even the direction of flow The working section incorporates three tappings on its top section to incorporate pitot tubes. These are located at the start of the working section, upstream and downstream of the model under test location All the optional and self-built models are inserted through a circular hatch of 160mm diameter. Each of the accessories supplied are built into individual hatches which incorporate an angular scale, enabling the models to be manually rotated to known angles Linear speed – 0-40m/s Working section Length: 600mm Width: 310mm Height: 310mm Axial fan power – Approx. 4kW Fan turning speed – 3000rpm Measuring ranges Manometer: 0-250mm H₂0 Wind speed: 0-40m/s Angle of inclination: +/- 180° Lift force: +/- 10N Drag force: +/- 10N Pitching moment: +/- 3N EXPERIMENTAL CONTENT Investigation of the development of the boundary layer on a flat plate by measurement of the total head distribution* C30-11 Manometer Bank / C30-12 Electronic Manometer Bank To convert a head measurement using a manometer to an equivalent pressure reading To demonstrate the use of a static pressure reading to determine tunnel air velocity C30-13 Lift and Drag Balance To measures the lift and drag forces (aerodynamic loads) C30-14 Pitot Static Tube Static pressure, dynamic pressure and total pressure To demonstrate the difference between Static pressure, Dynamic pressure and Total pressure and how Dynamic pressure can be used to determine air velocity To show how velocity varies in the test section because of the velocity profile C30-15 Wake Survey Rake Comparison of drag for shapes of equal equatorial diameter Visualisation of flow around different body shapes Measurement of the wake profile behind different shapes C30-16 /17-Asoft 3-Component Balance – armSOFT To measure lift, drag and moment forces C30-20 Lift and Drag Aerofoil Lift and Drag forces on a symmetrical aerofoil at different angles of attack To convert a head measurement using a manometer to an equivalent pressure reading To convert head and pressure readings to alternative engineering units To demonstrate the use of a static pressure reading to determine tunnel air velocity C30-22 Drag Models Drag forces on bluff and streamlined bodies Comparison of drag for shapes of equal equatorial diameter Visualisation of flow around different body shapes Measurement of the wake profile behind different shapes (requires C30-15) C30 Airplane Models, C30-35 Car Model Visualise airflow over various aircraft at different angles of attack Visualise airflow over a car C30-30-01,02,03,04,06,07 Wing Models Lift, Drag and Moment forces on a aircraft wing at different angles of attack To convert a head measurement using a manometer to an equivalent pressure reading To convert head and pressure readings to alternative engineering units To demonstrate the use of a static pressure reading to determine tunnel air velocity C30-30-02 Wing Model Type 2 NACA 633-618 (Requires C30-13 or C30-16/17) C30-31 Aerofoil Model with Flap (Requires C30-13 or C30-16/17) Effect of Lift, Drag and Moment forces on a aircraft wing with change of flap angle To investigate the effects of control surfaces such as flaps, ailerons, elevator, or rudder Influence of a flap C30-42 Winglets Kit (Requires C30-13 or C30-16/17) Wing Theory Lift, Drag and Moment forces on a aircraft winglet at different angles of attack Observation of eddies on winglets C30-23 Pressure Cylinder), C30-18-01 Cylinder with Pressure Tapping for 3600 Drive Flow around a cylinder To investigate the variation in Static Head resulting from a change in cross-section area The measurement of pressure distribution around a circular cylinder at different velocities (and Reynolds Number) C30-21 Pressure Wing NACA 0015, C30-32 Pressure Wing NACA 54118 Profile, C30-33 Pressure Wing NACA 4415 Profile Flow and pressure distribution around a symmetrical aerofoil at different angles of attack To investigate the pressure distribution across the wake behind the wing C30-24 Bernoulli Apparatus (requires C30-11 or C30-22) Effect of change in cross-section and application of Bernoulli equation To investigate the variation in Static Head resulting from a change in cross-sectional area To investigate the Bernoulli equation (if C30-14 Pitot Static Tube is also available) C30-25 Boundary Layer Plate (requires C30-11 or C30-22) Laminar and Turbulent Boundary Layer Development To measure the depth of the boundary layer on smooth and rough flat plates C30-34 Spring Mounted Wing Model Aeroelastic Flutter *additional accessory’s required dependant on experiment
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