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.



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.


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.



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.

Acoustic Resonance Tube

This is a device for investigating the response characteristics of the created pressure-sensitive paint. A speaker installed at one end of the tube generates pressure fluctuations of 150-10,000 Hz, and the response characteristics of the PSP are investigated by comparing the responses of the PSP and the semiconductor pressure sensor installed at the other end of the tube. A UV laser is used to excite the PSP, and a photomultiplier tube is used to detect the emission of the PSP. The responsiveness of the PSP can be investigated in the pressure range from 1 kPa to atmospheric pressure. The temperature of the PSP sample plate can also be controlled by a Peltier element.

Automatic Calibration System for PSP

This is a device for examining the pressure sensitivity and temperature sensitivity of the created pressure-sensitive paint. The emission intensity of PSP under various pressure and temperature conditions is captured by a CCD camera, and the static characteristics of the PSP can be investigated. The pressure in the chamber and the temperature of the table on which the sample plate is installed can be controlled precisely. The pressure and temperature ranges are 0.3-300 kPa and 263-333 K, respectively. It is also possible to conduct calibration with different oxygen concentrations.

Transonic and Supersonic Wind Tunnel (Common equipment for Department of Aerospace Engineering)

This is a suction-type supersonic wind tunnel. The size of the test section is approximately 80 mm high x 40 mm wide (height may vary slightly depending on the nozzle used). By changing the nozzle, wind tunnel experiments can be performed under the condition of Mach number 1.1 to 2.0.

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