The wind tunnel has a maximum local Mach number of 0.6 for the bypass model tested. In addition, discrete surface flow visualization (see below) is utilized in the facility to determine flow direction and regions of flow separation in the channels. This results in a complete mapping of the pressure field on the outer circumference and at complete radial/circumferential cross-sections at any axial location. Axisymmetric models are supported internally to allow the outer walls of the test section to rotate for static wall pressure measurements and radial sting probe measurements using pitot-static probes, hotwires, or 5-hole probes available in the laboratory. It has a contraction ratio of 63:1 and is driven by a 125 hp blower due to the high pressure loss. The axisymmetric transonic wind tunnel is an in-draft open circuit tunnel with an inner test section diameter and length of 11.1 inches and 9 feet, respectively. subsonic lab wind tunnels Axisymmetric Inlet/Bypass Transonic Wind Tunnel This wind tunnel can be utilized to perform experiments across a wide array of test articles, though it is commonly used to conduct aerodynamics experiments on airfoil and wing geometries. These instruments are supplemented by an array of additional capabilities, including advanced diagnostic measurement systems and multi-channel simultaneous sampling systems. This instrumentation includes an Aerotech 3-component balance, a DTC Initium pressure system with 160 measurement ports, a wake rake composed of 52 total pressure ports, a direct-drive pitching system for unsteady airfoil experiments, and a set of dedicated high-resolution pressure transducers and thermocouples to monitor wind tunnel conditions. The wind tunnel is operated from a dedicated control room directly adjacent to the wind tunnel high-bay area and is equipped with wide array of instrumentation for experiments. The tunnel is driven by a 150-hp electric motor connected to a 5-bladed fan, and it can be operated at speeds up to a maximum Mach number of 0.2 with a test-section turbulence intensity below 0.1% for all operating conditions. The test section features a 2.8-ft height and a 4-ft width, across an 8-ft length. The 2.8 ft x 4 ft wind tunnel is a low-speed, low-turbulence open-return wind tunnel. wind tunnel facility Subsonic Wind Tunnel (2.8 ft x 4 ft) This facility has been utilized in the past to study plasma assisted combustion, iced airfoil separation bubbles, flow field from heated stack plumes and other aerodynamic phenomena. The 4 foot long test section has excellent optical access for laser diagnostics and utilizes a dedicated 16 channel Netscanner PSI pressure transducer system to monitor total and static pressures of the tunnel and model. The tunnel has a high contraction area ratio resulting and low free stream turbulence and can operate up to a maximum Mach number of 0.4. This tunnel is particularly suited for diagnostic techniques which require particles or when conducting combustion experiments that result in products that need to be exhausted outside the laboratory. The 15”x15” wind tunnel at ARL is a fan-driven open-loop design that exhausts outside the laboratory. Contacts Faculty Researchersįacility and Equipment Description 15”x15” Subsonic Wind Tunnel Facility ARL has had a wide range of funding sources over the years including, AFOSR, ONR, NASA, DOE, Gulfstream, Rolls-Royce, 3M to name a few. Michael Selig and his students in this facility. Much of the performance data of low Reynolds number airfoils (UIUC Airfoil Data Site) and propeller performance curves (UIUC Propeller Data Site) were conducted by Prof. In recent years, research activities have included studies in unsteady aerodynamics, airfoil icing effects, flow control, motorsports aerodynamics, wind turbine blades, distributed propulsion systems, plasma assisted combustion, and turbojet bypass flows. The facility includes advanced instrumentation and flow diagnostics to allow researchers unique insight into the experimental models and flow regimes that are investigated. The Aerodynamics Research Laboratory (ARL) houses subsonic wind tunnels utilized to conduct research in aerodynamics, propulsion, and fundamental studies in fluid mechanics. Online MS/MEng in Aerospace Engineering.Master of Engineering in Aerospace Systems Engineering (M.Eng.).Career Placement & Professional Development.
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