A wind tunnel is a duct through which air is either blown or pulled out to simulate air flow over objects. The model of the object to be tested, called the prototype, is placed in the test section of the wind tunnel and the pressures, forces and moments experienced by the model at various wind speeds and in different orientation with reference to the wind are measured using special transducers. The results of wind tunnel measurements can be utilized to generate the design data for the prototype. Wind tunnels are useful research and educational tools for students to study problems related to several areas including fluid mechanics and aerodynamics. Low speed wind tunnels are employed for teaching and research in aeronautical, mechanical, automobile, civil, architectural, environmental and marine engineering departments of educational institutions.
Sci-tech Low Speed Wind Tunnel with a test section of 0.4m square Model AT 07 is a suction type open circuit wind tunnel designed to test models and to conduct teaching and basic research experiments related to fluid mechanics and aerodynamics. All tunnel components are supported on metal frames and include lockable castors for mobility. The wind tunnel components are constructed as per existing standard practices of wind tunnel construction and are made of wood and mild steel (suitably surface treated to avoid corrosion) construction. The inside surface will be smooth to ensure clean flow in the tunnel. The combination of bell mouth entry, settling chamber with honey comb and screens and nozzle contraction provide tunnel mean flow uniformity and turbulence values required for any basic and applied aerodynamic research. The square test section is removable and is designed for easy installation and changing of models, accessories and instrumentation. Transparent Plexiglas windows are provided to facilitate optical measurement techniques and flow visualization. Diffuser transition is designed to decelerate the flow without flow separation from the walls. The drive system consists of a six-bladed fan and a variable speed motor and controller. Wind tunnel test speeds up to about 40m/s can be obtained. Vibration during tunnel operation is minimized by suitable mounting of the fan drive system. The model support system is provided to position models in the test section and conduct tests at various angles of incidence. A three component floor mounted balance is provided to make force measurements. Model having standard geometrical details such as symmetric aerofoil section with surface pressure tapings is provided. Models will be selected based on the wind tunnel blockage considerations. Tunnel operation, control, data acquisition and processing of data are through a computer based system.
– Suction type, open circuit, horizontal wind tunnel.
– Test velocity range: 0.5 to 40 m/s (continuous).
– Total head variation: within +/- 0.5%.
– Mean flow uniformity: within +/- 0.3%.
– Boundary layer thickness: within 25 mm in the test section wall at 40m/s.
– Test section, 0.4m x 0.4m x 1.4m long, steel frame and fine quality wood construction with Plexiglas top and side windows, detachable.
– Bell mouth entry, 1.6m X 1.6m, wood.
– Setting chamber, 1.4m X 1.4m, wood.
– Honey comb (200mm deep and 15mm mesh).
– Screens, 3 Nos. stainless steel / Aluminum.
– Contraction, contraction ratio 12:1.
– Diffuser transition (wood) and safety screen (to protect fan).
– Axial flow fan, FRP, 6-bladed, 0.9m dia. with housing.
– DC motor fan drive with RPM controller equipped with a potentiometer for manual
operation, Approximately 20 kW, 1800 RPM, digital speed indicator and control unit. ( DC
motor with Thyristor controller can be supplied as option)
– 2-D Probe traverse, fitted with motorized vertical and horizontal traversing systems with a
digital position indicator for probes.
– Floor mounted model support and incidence mechanism – turn table, steel / Aluminum
– Control panel with digital display of fan drive and tunnel test parameters.
– PC based tunnel speed control and data acquisition system (32 channels).
– Software for pressure data and balance data reduction.
– Balance calibration software.
– Symmetric aerofoil model with surface pressure taps (No. of taps: 14), Aluminum.
– Circular cylinder model with pressure taps, Aluminum.
– Half wing model with pressure taps, Aluminum.
– Bridge model with pressure taps, Aluminum.
– Automobile model with pressure taps, Aluminum.
– Building model with pressure taps, Aluminum.
– Force measurement model of symmetric airfoil
Accessories Probes and Instrumentation:
– Static pressure taps on test section top wall (at 100mm intervals).
– Pitot probe (2Nos.) with mountings, stainless steel / brass.
– Pitot-static probe (2Nos.) with mountings, stainless steel / Aluminum / brass.
– Multi-tube water manometer, 10 tubes, 500mm long, consisting of glass pipes, PVC tubes, Perspex reservoir and steel frame.
– Low pressure electronic differential pressure transducer and 32 channel scanning device.
– Wake rake for wake survey, 12 probes, stainless steel / brass.
– Boundary layer probe, stainless steel tubes / brass.
– Noise detector.
– Smoke generator and rake set.
– Three Component Balance, Data Acquisition System and Instrumentations, external floor mounted strain gage type, with signal conditioning unit, computer based data acquisition, instrumentation system and digital display. Range: Drag: +/-70N, Lift: +/- 1500N and pitching moment: +/- 70 Nm. (Balance of any other ranges can be supplied on request). Full scale output (before amplification): about 2 mV/V excitation
– Motorized system with stepper motor control for changing model incidence.
– Balance calibration system.
– Connectors and tubing.