Experimental Facilities

Tohoku-University Basic Aerodynamic Research Wind Tunnel (T-BART)

Tohoku-University Basic Aerodynamic Research Wind Tunnel (T-BART) is a low-speed wind tunnel that can conduct wind tunnel tests with high-reliability. The wind tunnel is a suction Eiffel-type wind tunnel with a 300 x 300 x 760 mm test section that minimizes noise in the test section. The range of the flow velocity is 5-60 m/s, and the turbulent intensity in the test section is less than 0.5%. The test sections can be easily reconfigured and are used for a variety of experiments, including aerodynamic measurements and visualization experiments.

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Mars Wind Tunnel (MWT)

Mars Wind Tunnel (MWT) is a wind tunnel that can reproduce a kind of extreme flow, the compressible low Reynolds number flow. The total wind tunnel pressure can be changed (Pt = 1-60 kPa), and the working fluid can be replaced by carbon dioxide. The test section is 150 × 100 × 600 mm rectangular section, and the wind tunnel is driven by an ejector installed in the downstream of the test section. We have achieved a compressible low-Reynolds-number flow with a Mach number of 0.1-0.74 under low-pressure conditions. The wind tunnel is used for experiments simulating the flow around an aircraft flying in the Martian atmosphere and for fundamental study on compressible low-Reynolds-number flow.

火星大気風洞グループHP用研究紹介

Magnetic Balance and Suspension System (MSBS)

Magnetic Balance and Suspension System is a balance device that supports a model by magnetic force in a non-contact manner. The absence of mechanical support allows wind tunnel testing without interference between the support and the airflow. Furthermore, it is possible to measure the aerodynamic force acting on the model from the current flowing through the coil used for levitation. By using a wireless pressure measurement system and particle image velocimetry, a measurement can be performed while maintaining non-invasiveness. This system has a square test section of 300 × 300 mm and is connected to T-BART when conducting the wind tunnel tests.

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Supersonic jet generator and Anechoic Chamber

The supersonic jet generator can reproduce a supersonic jet with a maximum Mach number of approximately 2.1 by discharging compressed air into the atmosphere. This device is used to study the exhaust flow of a rocket engine. An anechoic chamber is a device that can suppress the reflection of the sound generated in the room and is used for sound source identification. The internal dimensions are about 3 × 3 × 3 m, and the visualization windows for various experiments are set up for 270 degrees around the anechoic chamber, enabling visualization and measurement from multiple directions.

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