Equipment

B : Fluid thermodynamics-related facilities
Fig.1 NPL type blow-down wind tunnel
Fig.1 NPL type blow-down wind tunnel

NPL type blow-down wind tunnel
The low speed wind tunnel is the NPL type blow-down wind tunnel which has a 0.6m hight x 0.6m width and is used extensively for academic research work. The maximum flow speed is 35m/s, and the turbulence intensity of free stream is less than 0.3%.


Fig.2 Small Blow-down wind tunnel
Fig.2 Small Blow-down wind tunnel

Small Blow-down wind tunnel
The blow down wind tunnel is used for a variety of research work and a traversing equipment of pitot tube and hot-wire probe has been installed for velocity measurement system. The measurement duct is exchangeable. The characteristics of turbulence are investigated to clarify the flow mechanism of the laminarization and the re-transition.


Fig.3 Closed-circuit water tunnel
Fig.3 Closed-circuit water tunnel

Closed-circuit water tunnel
The water tunnel is a closed circuit facility with a 2.0 m x 0.3 m x 0.15 m working section and is operating at water speed up to 0.4m/s, and is equipped with a PHF probe and a LDV system for skin friction measurement and flow visualization. This facility is utilized in order to clarify flow mechanism of the reduction of the skin friction drag over the compliant wall is now conducted using this facility.


3D-PTV measurement system
PTV measurement system is composed of two CCD cameras (Sony XC-77R), two laser disk recorder (Sony LVR) and a video capture board (IO-DATA GV-VCP/PCI). A series of TV frames taken by the cameras is consecutively recorded onto the laser disks. At the data reduction, replayed image are A/D converted by the image processor and then transferred to a PC. Photographic coordinates and 3-D trajectories of the tracer particles are calculated using the original software.

Fig.4 3D-PTV measurement system
Fig.4 3D-PTV measurement system
Fig.5 Image processing software for PTV experiments
Fig.5 Image processing software for PTV experiments

Fig.6 LPX150T/LAVISION SYSTEM
Fig.6 LPX150T/LAVISION SYSTEM

Laser Induced Fluorescence System
This laser system measures the non-equilibrium atoms and molecules of O, H, OH, O2, NO in flames and reactive shock waves two- and three-dimensionally using a double-pulse YAG laser and two Dye lasers together with two ICCD cameras.


Pulse Detonation Engine

Pulse Detonation Engine
This is a next aerospace transport system applied detonation phenomena. Since PDE is very simple for its structure and operating cycle, it is expected that PDE will become the next aerospace engine.

Fig.7 PULSE DETONATION ENGINE SYSTEM


Hypersonic Shock Tube

Hypersonic Shock Tube
This is a devise for supersonic shock tube experiment applied free-piston driving method. Using this devise, artificial atmosphere ranging from 10 to 20 with Mach number can be obtained.

Fig.8 HYPERSONIC SHOCK TUBE SYSTEM


Turbulent Combustion Control System
Fig.9 COMBUSTION CONTROL SYSTEM

Turbulent Combustion Control System
This is a system to control oscillatory combustion observed with turbulent combustion. Active combustion control system is developed using a sensor and an actuator. This system is applied to a jet engine for aerospace vehicle.


Liquid Nitrogen Automobile System

Liquid Nitrogen Automobile System
This is a zero-emissions automobile using liquid nitrogen as its fuel. The liquid nitrogen is supplied from LN2-tank, and then vaporized and heated by ambient air through a heat exchanger system. This devise is driven by an air motor to supply the vaporized LN2.

Fig.10 LIQUID NITROGEN AUTOMOBILE SYSTEM


Constant Temperature Room

Constant Temperature Room
The constant temperature room has the dimensions of W3470×D2570×H2200. The room temperature can be maintained constant between -35° and 80° Celsius. Experiments of melting of the ice packed bed and forming of hydrate are carried out in the room. The room is very useful to do various experiments under temperature controlled accurately.

Fig.11 Constant Temperature Room

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