J-GLOBAL ID:201110005204475760   Research Resource code:5000003253 Update date:Nov. 01, 2004

0.44m Hypersonic Shock Tunnel

Owning Organization:
Contact: HAMAMOTO Shigeru
Resource classification: Experience equipment, Facilities, etc
Shock tunnel with 44 cm of diameter of nozzle exit.
Mach number of 10 and 12.
Constructed in 1967, and relocated and renovated in
Type: Two stage compression shock tunnel/shock tunnel
with a diaphragmless driver section
Use: Aerodynamic research at hypersonic speed, and
measurement of aerodynamic heating
User procedures and method:
Refer to Web Page of JAXA.

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