Demonstration of the Aerodynamic and Electronic Component Cooling Design in a Subsonic Wind Tunnel

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The Research and Consultancy Committee of engineering department organized a training programme “Demonstration of the Aerodynamic and Electronic Component Cooling Design in a Subsonic Wind Tunnel” on 7th April 2022 at 12 Noon. Dr Arthur Davis Nicholas, Lecturer, Engineering department, organized this program and demonstrated the working nature of “Subsonic wind tunnel” which was erected in the welding workshop. This training session is a part of the research outcome of a TRC funded RG project “Optimization of Wind Turbine Blade Nomenclatures Using a Subsonic Wind Tunnel Facility”. The session was well received by the staff members with very good interaction. Around 23 staff members were participated in this event.   

Here, you can find the brief of the wind tunnel facility that is functioning in the welding workshop.

Despite advances in computational aerodynamics, wind tunnels are and will continue to be a cornerstone in the design process for a wide range of Aerodynamics applications. This mostly stems from the difficulties of accurately and efficiently predicting turbulent flow fields computationally. To expand in-house aerodynamics capabilities, a general-purpose low-speed wind tunnel was designed and built in Welding Lab, Engineering Department, University of Technology and Applied Sciences. This wind tunnel is designed to reach test section speeds of up to around 80 m/s. To aid in the initial design, semi-empirical formulas are used to estimate aerodynamic efficiencies and the required fan-blower power as a function of various design choices. Tunnel geometry is selected to optimize test section air flow quality, test section size, and diffuser angle (to avoid boundary layer separation), while the overall tunnel size is constrained to fit in the allotted laboratory space. The proposed closed-circuit wind tunnel is vertically oriented to reduce footprint, and is 6.56 m long, includes a convergent, test section, divergent and honey comb structure. Convergent is designed at 2.1 X 2.1 m inlet cross-section with honey comb structure built for a 0.3 m depth. Test section is built at 0.5 X 0.5 m cross-section and 1 m length. It is followed by a divergent, with exit section of 1.7 X 1.7 m cross-section. Air flow is induced by a 7.5 hp 3 PH, 360 rpm, and squirrel cage induction motor driven exhaust fan of 1.6 m diameter. An MS 300 Delta VFD is set to regulate the rpm of the exhaust fan. A set of probe type velocity sensors, probe type temperature sensors and static pressure sensors are added to the test section facility to organize the flow inside the test section. A MSHRIY 8 channel data logger is connected to the sensors to read the flow conditions. Testing of Aerofoils for aircraft wing and wind Turbine Blades along with Vehicle Aerodynamics and Heat Sink testing can be performed in this wind tunnel facility. Currently, a batch of bachelor students are carrying out experimental analysis of NACA 4412 is tested for its characteristics.


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Thursday, 28 April 2022 00:00 Written by  Dr G. Kumaravel In Engineering
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