JAXA has a range of testing facilities essential for aeronautics, such as wind tunnels, research aircraft, aeroegine test facilities, composites test facilities and supercomputer. Some test facilities are available to external users.
Wind tunnels are fundamental tools for studying aerodynamics and fluid flow phenomena. JAXA has one of the largest cluster of wind tunnels in Japan, offering a range of testing environments for aircraft and spacecraft.
The wind tunnel facilities are used to study aerodynamic characteristics (aerodynamics) and flow phenomena of the air surrounding aircraft or spacecraft. Airflow around aircraft can be simulated in a wind tunnel by exposing a model to the artificially created airflow in a wind tunnel. Wind tunnel tests can measure aerodynamic forces acting on the model, pressure distributions around airframe and so on.
JAXA operates wind tunnels of various sizes and types, providing a wide ranged test conditions from low speeds to hypersonic speeds, and even to the severe atmospheric re-entry environment with particular air-flow.
Designed to examine the aerodynamic characteristics of aircraft at low speeds (speeds of takeoff and landing etc), this is the largest low-speed wind tunnel for aircraft in Japan.
Type: Continuous, Atomospheric
Test section: 6.5m (H) x 5.5 m (W)
Speed: 1-70m/s
This low-speed wind tunnel has a compact sized test section and has been used for various tests from basic aerodynamic measurements to the tests simulating flutter conditions using gust wind cart. The test section can be converted into an anechoic cart for acoustic measurements and noise source measurements.
Type: Continuous, Atomospheric
Test section: 2m(H)x2m(W)x4m(L)
Speed: 3 – 60m/s (continuous), max. 67m/s
This wind tunnel can produce transonic flow up to Mach number of 1.4, and has been used to measure aerodynamic characteristics of aircraft and launch vehicles flying at transonic speed. The test section can be fitted with one of four interchangeable inner carts depending on test purpose. This is the largest transonic wind tunnel in Japan.
Type: Continuous, Pressurized
Test section: 2m(H)x2m(W)
Speed: Mach 0.1-1.4
This wind tunnel can create supersonic flow between Mach 1.4 and 4.0, and has been used to study aerodynamic characteristics for supersonic transport, launch vehicles and spacecraft that experience this speed range.
Type: Blow down
Test section: 1m (H) x 1m (W)
Speed: Mach 1.4 – 4.0
Consisting of two hypersonic wind tunnels, this facility is used to study aerodynamic characteristics and aerodynamic heating for hypersonic vehicles. The 0.5m hypersonic wind tunnel has interchangeable nozzles to create airflow of Mach 5 and Mach 7, while the 1.27m hypersonic wind tunnel has a fixed Mach 10 nozzle.
Type: Blow-down/ Vacuum intermittent
Nozzle exit diameter: 0.5m / 1.27m
Speed: Mach 5, 7/ Mach 10
These wind tunnels can create high-enthalpy conditions for re-entry vehicles, and are used for the heating testing of thermal protection system for re-entry vehicle with high-enthalpy flow etc.
■750kW Arc-heated Wind tunnel
Type: Segmented arc-heated
High enthalpy (up to around 30MJ/kg)
Nozzle exit diameter: 11.5cm
Speed: Mach 4.8 (designed)
■110kW ICP-heated Wind tunnel
Type:Inductively coupled plasma
High enthalpy (up to around 20MJ/kg)
Test chamber: Free jet type
Speed: Subsonic
This wind tunnel can create transonic flow with high Reynolds number. The Reynolds number can be varied by changing the stagnation pressure.
Type: Blow down
Test section: 0.8m(H)x0.45m(W)
Speed: Mach 0.2 – 1.4
This facility is used to examine transonic flutter phenomena.
Type: Blow-down
Test section: 6m(H)x0.6m(W)
Speed: Mach 0.5 - 1.2
The tunnel has been used for various studies, such as the studies on boundary‐layer transition and the tests on aerodynamics of unmanned aircraft systems as well as for the development of advanced measurement technology like pressure‐sensitive paint (PSP).
Type: Closed circuit
Test section: .65m(H)x0.55m(W)x1.5m(L)
Speed : 5‐50m/s
